Federal Register / Vol. 54, No. 95 / Thursday, May 18, 1989 / Rules ...

601 East 12th Street, Kansas City, Missouri 64106. FOR FURTHER IN FO RM ATIO N CONTACT: Mr. Charles Riddle, ACE-140W, Aerospace Engineer, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone 316-946-4427. SUPPLEMENTARY INFO RM ATIO N: This amendment revises AD 87-21-02, Amendment 39-5740 which required modification to the fuel filler ports on Cessna 300 and 400 Series airplanes equipped with reciprocating engines. Some confusion has apparently been prevalent concerning the applicability of this AD to the Model T310 and to the early Model 310 airplanes. Although these models are covered by the serial number listing the FAA has determined that the list of affected airplanes and corresponding serial numbers needs clarification. Therefore, the FAA is revising AD 87-21-02 by adding a T310 models reference and by providing a more detailed breakdown of the applicable serial numbers for the Model 310 airplanes. 21416 Federal Register / Vol. 54, No. 95 / Thursday, May 18, 1989 / Rules and Regulations Since this amendment provides clarification only, and imposes no additional burden on any person, notice and public procedure hereon are unnecessary, and the amendment may be made effective in less than 30 days. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. The FAA has determined that few if any small entities will experience a significant financial impact as a result of this proposal. Therefore, I certify that this action (1) is not a “major rule” under Executive Order 12291, and (2) is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR11034; February 26,1979). A copy of the final evaluation prepared for this action is contained in the regulatory docket. A copy of it may be obtained from the Regional Rule Docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends § 39.13 of Part 39 of the FAR as follows: PART 39—[AMENDED] 1. The authority citation for Part 39 continues to read as follows: Authority: 49 U.S.C. 1354(a), 1421 and 1423; 49 U.S.C. 106(g) (Revised, Pub. L. 97-449, January 12,1983); and 14 CFR 11.89. § 39.13 [Amended] 2. By revising and reissuing AD 87-21- 02, Amendment 39-5740, as follows: Cessna: Applies to the following airplanes equipped with reciprocating engines certificated in any category: Model Serial Number T303 ................... .. T30300001 thru T30300301 310D..................... 39032 thru 39299 310E ........... .......... 310M0001 thru 310M0036 310F ................i.... 310-0001 thru 310-0156 310G thru 310R.... 310G0001 thru 310R2140 (Including T310P, T310Q and T310R) 320 thru 320F ...... 320-0001 thru 320F0045 Model Serial Number 335......... ............... 335-0001 thru 335-0065 340 thru 340A...... 340-0001 thru 340A1543 401 thru 401B....... 401-0001 thru 401B0221 402 thru 402C..... . 402-0001 thru 402C0653 404.....................;... 404-0001 thru 404-0859 411 thru 411A ..... 411-0001 thru 411A0300 414 thru 414A ..... 414-0001 thru 414A0858 421 thru 421C ...... 421-0001 thru 421C1257 Compliance: Required as indicated in the body of the AD, unless already accomplished per the unrevised version of this AD. To preclude misfueling of the airplane resulting in engine failure, accomplish the following: (a) Within the next 12 calendar months after the effective date of this AD, unless already accomplished, modify all fuel filler opening(s) in accordance with the instructions contained in Cessna Service Information Letter ME84-31 dated July 20, 1984. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) In accordance with FAR Part 43, Appendix A, Item (c) 29, the modifications required by this AD (except installation of the SK303-29 kit) is preventative maintenance and may be performed by the holder of a pilot certificate issued under FAR Part 61 on airplanes owned or operated by him subject to the limitations of FAR 43.3(a). The maintenance record entries required by FAR 43.9 and FAR 91.173 must be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Cessna Aircraft Company, Customer Services, Post Office Box 1521, Wichita, Kansas 67201; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This Amendment revises AD 87-21- 02, Amendment 39-5740. This amendment becomes effective on June 16,1989. Issued in Kansas City, Missouri, on May 3, 1989. Barry D. Clements, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 89-11852 Filed 5-17-89; 8:45 am] BILLING CODE 4910-13-M 14 CFR Part 39 [Docket No. 89-NM-64-AD; Arndt. 39-6216] Airworthiness Directives; McDonnell Douglas Model DC-9-15F, -32F, -33F, and -34F Series Airplanes, Including C-9A and C-9B (Military) Airplanes a g e n c y : Federal Aviation Administration (FAA), DOT. a c t i o n : Final rule. SUM M ARY: This amendment supersedes an existing airworthiness directive (AD) applicable to certain DC-9 series airplanes which currently requires inspection and modification of the main cargo door hydraulic control valve and control panel access door. This amendment also replaces the requirements of another existing AD and requires (1) inspection and modification of the main cargo door hydraulic control valve and control panel access door, (2) visual inspection of the main cargo door to ensure the door is locked prior to each takeoff, (3) inspection and modification of the exterior markings on the main cargo door, and (4) functional checks of the door-open indicating system. This AD is prompted by a recent accident in which the main cargo door opened in flight. This condition, if not corrected could result in loss of pressurization and control of the airplane. DATES: Effective May 30,1989. ADDRESSES: The applicable service information may be obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California, Attention: Director of Publications, C1-L00 (54-60). This information may be examined at FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or 3229 East Spring Street, Long Beach, California. FOR FURTHER IN FO RM A TIO N CONTACT: Mr. Robert M. Stacho, Aerospace Engineer, Systems and Equipment Branch, ANM-131L, FAA, Northwest Mountain Region, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; telephone (213) 988-5338. SUPPLEMENTARY IN FO RM A TIO N : In 1975, FAA issued AD 75-03-03. Amendment 39-2076, to require inspection, modification, and replacement, if necessary, of the main cargo door hydraulic control valve and control panel access door spacer on McDonnell Douglas Model DC-9 series airplanes. That action was prompted by the inadvertent opening of the main cargo Federal Register / Vol. 54, No. 95 / Thursday, May 18, 1989 / Rules and Regulations 21417 door on a Model DC-9 series airplane during flight. This condition, if not corrected, could lead to loss of pressurization and control of airplane. In 1984, FAA issued AD 84-23-02, Amendment 39-4953, applicable to both Model DC-8 and DC-9 series airplanes, to require visual inspection of the main cargo door to ensure it is closed, latched, and locked prior to each takeoff, or modification of the original, and installation of a second door-open indicating system. Since the issuance of those two AD’s, an accident involving a model DC-9 series airplane recently occurred in which the main cargo door inadvertently opened during takeoff or shortly thereafter. This has prompted the FAA to further review the Model DC-9 main cargo door, including the main cargo door design, prior incidents of inadvertent openings of main cargo doors in flight, maintenance of the door, all available service information, and the existing airworthiness directives concerning the Model DC-9 main cargo door. The FAA has determined that some Model DC-9 airplanes may not have proper exterior markings on the main cargo door, which are necessary to determine visually that the door is properly closed, latched, and locked. In addition, on some airplanes the exterior markings are not easily seen because of the blending background color, especially under night lighting conditions. Also, the FAA has been advised that some crew members simply lean outside the main entrance door to visually check that the latch controls on the cargo door are in the locked position. A door-locked indication can not be properly ascertained from the main entrance door. The airplane involved in the accident described above did not have the dual door-open indicating system installed; its operator opted to rely on the visual inspection method of AD compliance. Aircraft which do not have the dual door-open indicating system (described in McDonnell Douglas Service Bulletin 52-92} installed could have a latent failure condition in the original door- open indicating system such that the door-open annunciating light can extinguish with the cargo door merely resting on the door jamb in the closed, but not latched and locked, position. Also, properly securing the main cargo door hydraulic control panel access door can prevent inadvertent movement of the hydraulic control valve operating handle which is used to activate (open) the main cargo door. Based on the FAA review of the main cargo door design, operation, and maintenance, the FAA has determined that additional inspections, modifications, and checks are necessary to ensure that the Model DC-9 main cargo door is properly closed, latched, and locked prior to flight. The FAA has reviewed and approved McDonnell Douglas All Operators’ Letters (AOL) 9-799, dated April 16, 1974, 9-799A, dated January 22,1975, and Service Bulletin 52-92, Revision 2, dated November 21,1985, which describe inspections, modifications, and checks of the main cargo door hydraulic control valve and control panel access door, the original door-open indicating system, and the dual door-open indicating system. The FAA has also approved the exterior markings on the main cargo door which are used when visually determining that the door is closed, latched, and locked. McDonnell Douglas has also developed additional safety features to prevent the door from opening in flight. The FAA has reviewed and approved McDonnell Douglas Service Bulletin 52- 91, Revision 2, dated August 12,1976, which describes installation of a hydraulic isolation valve to shut off the hydraulic pressure to the control valve when the system is not in use; Service Bulletin 52-93, Revision 1, dated May 3, 1978, which describes installation of a viewing window in the exterior skin of the door for visual inspection of the lockpin position; and Service Bulletin 52-100, dated September 30,1976, which describes installation of a vent door to improve the positive lock feature of the cargo door latching and locking system and limit pressurization of the airplane. Since this condition is likely to exist or develop on other airplanes of the same type design, this AD supersedes AD 75-03-03; is different from and replaces the requirements of AD 84-23- 02 for Model DC-9 series airplanes only; and requires additional inspections, modifications, and checks of the main cargo door. All requirements currently imposed by AD 75-03-03 are incorporated into this AD. The requirements of this AD differ from and replace the requirements of AD 84-23-02 for Model DC-9 airplanes only by requiring the operator to document compliance with the visual check requirement to ensure that the door is closed, latched, and locked prior to takeoff; deleting the requirement that a flight crew member, a mechanic, or a ramp supervisor ensure that the main cargo door is closed, latched, and locked prior to takeoff, placing that responsibility on the operator; and requiring that the visual check of the exterior manual latch controls be accomplished from outside the airplane. In addition, the operator must provide qualified personnel and training on the door closing, latching, and locking procedures as well as documentation of compliance with this AD. This AD also requires additional inspection, modification and checks by requiring initial and repetitive checks of the original door-open indicating system; initial and repetitive inspections of the main cargo door control panel access door and “T” handle clip; and inspection and modification, if necessary, of the main cargo door exterior lockpin handle and latch actuating socket markings. Accomplishment of the modifications specified in McDonnell Douglas Service Bulletins 52-91, 52-92, 52-93, and 52-100 will terminate certain inspections and checks required by this ÀD. The FAA considers the requirements of this AD as interim measures. The FAA is currently evaluating all available modifications to the main cargo door system, as well as other actions, and may propose additional mandatory corrective actions to ensure that the Model DC-9 main cargo door will not inadvertently open in flight. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. The FAA has determined that this regulation is an emergency regulation and that it is not considered to be major under Executive Order 12291. It is impracticable for the agency to follow the procedures of Order 12291 with respect to this rule since the rule must be issued immediately to correct an unsafe condition in aircraft. It has been further determined that this document involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034; February 26,1979). If this action is subsequently determined to involve a significant/major regulation, a final regulatory evaluation or analysis, as appropriate, will be prepared and placed in the regulatory docket (otherwise, an evaluation is not required). List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. 21418 Federal Register / Vol. 54, No. 95 / Thursday, M ay 18, 1989 / Rules and Regulations Adoption of The Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends Part 39 of the Federal Aviation Regulations as follows: PART 39—[AMENDED] 1. The authority citation for Part 39 continues to read as follows: Authority: 49 U.S.C. 1354[a), 1421 and 1423; 49 U.S.C. 106(g) (Revised Pub. L. 97-449, January 12,1983); and 14 CFR 11.89. § 39 .13 [A m e n d e d ] 2. Section 39.13 is amended by superseding AD 75-03-03, Amendment 39-2076, with the following new airworthiness directive: McDonnell Douglas: Applies to Model DC-9- 15F, -32F, -33F, -34F, including C-9A and C-9B (Military) series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent inadvertent opening of the main cargo door in flight, a condition which could result in loss of pressurization and control of the aircraft, accomplish the following: A. Within the next 14 days after the effective date of this AD, ensure that the main cargo door is closed, latched, and locked prior to takeoff following each operation of the door, in accordance with the procedures specified below. The procedures required by this paragraph must be accomplished by qualified and trained personnel, and the training program must be approved by the FAA Principal Maintenance Inspector (PMI). The method for documentation of compliance must also be approved by the FAA PMI. 1. From the outside of the airplane, perform a visual check of the exterior manual latch controls, to ensure that the latch actuating socket and the lockpin handle are in the LOCK position; or 2. Perform a visual check of the latches and lockpins, located on the inside of the main cargo door, to ensure that the latches are in the closed position and the lockpins are in the locked position. 3. Prior to taxi, communicate to the flight crew that the main cargo door has been closed, latched, locked, and checked. B. Unless the modifications described in paragraph F. of this AD have previously been accomplished, within the next 30 days after the effective date of this AD, and thereafter at intervals not to exceed 45 days, conduct a main cargo door-open indicating system functional check in accordance with Paragraph 1 of McDonnell Douglas All Operator’s Letter (AOL) 9-799, dated April 16,1974. If the main cargo door-open indicating system functional check is not successfully accomplished, repair the main cargo door-open indicating system prior to further flight, in accordance with AÔL 9-799. C. Within the next 30 days after the effective date of this AD, and thereafter at intervals not to exceed 45 days, inspect and modify the main cargo door control panel access door, spacer block, and “T” handle stowage clip, in accordance with McDonnell Douglas AOL 9-799A, dated January 22,1975, and Paragraph 2.A. of AOL 9-799, dated April 16.1974, In addition, inspect the control panel access door to ensure the door can be secured in the down and locked position. If the control pane access door can not be secured in the down and locked position, repair prior to further flight. D. Unless previously accomplished in accordance with paragraph (2) of AD 75-03- 03, Amendment 39-2076, within the next 30 days after the effective date of this AD, verify that the main cargo door hydraulic control valve shaft operates freely, without binding, between the operate neutral and neutral lock positions. This shall be accomplished by opening the main cargo door hydraulic control valve control panel access door; raising the "T” handle Douglas P/N 4777888- 1, and pulling the “T” handle vertically upward to its maximum travel (operate neutral position). When the vertical force on the “T” handle is relieved, the main cargo door hydraulic control valve shaft should return to the neutral lock (down) position without binding. Replace the main cargo door hydraulic control valve, Douglas P/N 5919985-5001, prior to further flight, if the valve shaft does not return freely to the neutral lock position. E. Within the next 30 days after the effective date of this AD, inspect the main cargo door exterior lockpin handle and latch actuating socket markings in accordance with McDonnell Douglas AOL 9-799, dated April 16.1974, paragraph 4.C.; and McDonnell Douglas Drawings 7910689, Revision P, dated November 29,1973, item numbers 16 and 18 (DC-9-15F), or 7910868, Revision AK, dated January 21,1977, item numbers 16 and 18 (DC-9-32F, -33F, and -34F). If the exterior markings are not correct, modify in accordance with the above noted McDonnell Douglas drawings prior to further flight. F. Compliance with the requirements of paragraph B., may be terminated upon the installation of a main cargo door-open indicating circuit that utilizes a proximity switch, revision of the existing main cargo door-open indicating circuit, and the installation of a main cargo door indicating system test circuit, as outlined in the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 52-92, Revision 2, dated November 21,1985. G. Compliance with the requirements of paragraphs A., B., and F. may be terminated upon installation of the modifications to the main cargo door systems, in accordance with McDonnell Douglas Service Bulletins 52-91, Revision 2, dated August 12,1976; 52-92, Revision 2, dated November 21,1985; 52-93, Revision 1, dated May 3,1978; and 52-100, dated September 30,1976. H. The checks and modifications specified in paragraphs A. through G. of this AD are not required on airplanes which have the main cargo door deactivated and secured in the closed and locked position in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, until that door is reactivated. I. Compliance with the requirements of this AD constitutes terminating action for the requirements of AD 84-23-02, Amendment 39-4953, for Model DC-9 series airplanes only. Note: The requirements of AD 84-23-02 relating to Model DC-8 series airplanes are not affected by this AD. J. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. Note: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. K. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California, Attention: Director of Publications, C1-L00 (54-60). This information may be examined at FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or 3229 East Spring Street, Long Beach, California. This amendment becomes effective May 30, 1989. Issued in Seattle, Washington, on May 4, 1989. Leroy A. Keith, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 89-11865 Filed 5-17-89; 8:45 am] BILLING CODE 4910-13-M 14 CFR Part 39 [D o c k e t N o. 8 9 -A N E -0 9 ; Arndt. 3 9 - 6 2 t 4 ] Airworthiness Directives; Textron Lycoming Model TIO-540-S1AD Reciprocating Engines a g e n c y : Federal Aviation Administration (FAA), DOT. a c t i o n : Final rule. s u m m a r y : This amendment adopts a new airworthiness directive (AD) which requires initial and repetitive inspections of exhaust system flanges, on Textron Lycoming Model TIO-540- SlAD reciprocating engines until a modified crossover exhaust tube assembly is incorporated. The AD is needed to prevent possible cracking of