Airworthiness Directives; The Boeing Company Model 747 Airplanes, 54405-54408 [2011-22371]

Download as PDF Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules Comments Due Date (a) We must receive comments by October 17, 2011. Affected ADs (b) None. Note 1: There is a warranty expiration date for the replacement of the actuators. The FAA recommends owners/operators that have affected main landing gear actuators contact the manufacturer immediately and replace the actuators under warranty. Applicability FAA AD Differences (c) This AD applies to PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P–180 airplanes, all serial numbers, that are: (1) Certificated in any category; and (2) have installed any of the following main landing gear (MLG) actuators: (i) Messier-Dowty Part Number (P/N) 114346003 (left hand side): with serial number (S/N) SA0706275, SA0706276, SA0706726, SA0706727, SA0706728, SA0706729, SA0706738, SA0706739,SA0707243, SA0707864, or SA0708072; or (ii) Messier-Dowty P/N 114346004 (right hand side): with S/N SA0703800, SA0703801, SA0705520, SA0706219, SA0706960, or SA0706961. Note 2: This AD differs from the MCAI and/or service information as follows: The compliance times of the MCAI are presented in flight cycles (landings). When doing the conversion for these airplanes from flight cycles to hours TIS, the FAA has estimated that 1 flight cycle is equal to 1 hour TIS based on the utility of this class of airplane. Since operators of aircraft of U.S. registry are required to keep track of hours TIS, the compliance time of this AD is in hours TIS. Subject (d) Air Transport Association of America (ATA) Code 32: Landing Gear. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Some lock sleeves (part number (P/N) 114146681), which were installed in some Main Landing Gear (MLG) actuators, had been incorrectly manufactured. If left uncorrected, this condition could lead to failure to lock the MLG actuator or to its unlock from the correct position, with subsequent possible damage to the aeroplane and injuries to occupants during landing. This AD requires replacing defective MLG actuators with serviceable ones. Defective actuators can be repaired by the manufacturer and identified with the ‘‘P180– 32–29’’ marking on the name plate. emcdonald on DSK2BSOYB1PROD with PROPOSALS Actions and Compliance (f) Unless already done, do the following actions: (1) Within 25 hours time-in-service (TIS) after the effective date of this AD, inspect both installed MLG actuators to determine if an affected P/N and S/N actuator is installed. (2) If any affected P/N and S/N actuator is identified with the ‘‘P180–32–29’’ marking on the name plate, no further action is required by this AD on that actuator. (3) If one or both affected MLG actuators are not identified with the ‘‘P180–32–29’’ marking on the name plate, before reaching a total of 3,000 hours TIS on the actuator or within the next 150 hours TIS after the effective date of this AD, whichever occurs later, replace the affected actuator(s) with serviceable parts following Part B of the Accomplishment Instructions of Piaggio Aero Industries S.p.A. Mandatory Service Bulletin No. 80–0304, dated July 9, 2010. (4) After the effective date of this AD, do not install any MLG actuator having an affected P/N and S/N, unless it is identified with the ‘‘P180–32–29’’ marking on the name plate. VerDate Mar<15>2010 16:04 Aug 31, 2011 Jkt 223001 Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329– 4090; e-mail: mike.kiesov@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 2011–0133, dated July 12, 2011; and Piaggio Aero PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 54405 Industries S.p.A. Mandatory Service Bulletin No. 80–0304, dated July 9, 2010, for related information. For service information related to this AD, contact Piaggio Aero Industries S.p.A Airworthiness Office; Via Luigi Cibrario, 4–16154 Genova–Italy; telephone: +39 010 6481353; fax: +39 010 6481881; E-mail: airworthiness@piaggioaero.it. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on August 26, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–22387 Filed 8–31–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0915; Directorate Identifier 2011–NM–020–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 747 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD would require repetitive general visual inspections for broken or missing latch pins of the lower sills of the forward and aft lower lobe cargo doors; repetitive detailed inspections for cracking of the latch pins; and corrective actions if necessary. This proposed AD was prompted by reports of fractured latch pins found in service; investigation revealed that the cracking and subsequent fracture were initiated by fatigue and propagated by a combination of fatigue and stress corrosion. We are proposing this AD to detect and correct fractured or broken latch pins, which could result in a forward or aft lower lobe cargo door opening and detaching during flight, and consequent rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by October 17, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. SUMMARY: E:\FR\FM\01SEP1.SGM 01SEP1 54406 Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. emcdonald on DSK2BSOYB1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: (425) 917–6428; fax: (425) 917–6590; e-mail: nathan.p.weigand@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2011–0915; Directorate Identifier 2011– NM–020–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of fractured latch pins found in service; investigation revealed that the cracking and subsequent fracture were initiated by fatigue and propagated by a combination of fatigue and stress corrosion. One operator reported a fractured latch pin of the lower sill of the aft lower lobe cargo door; the fracture initiated from a crack on the pin’s internal diameter. Part of the pin was found on the ground during an airplane walk-around. The airplane had accumulated 75,495 total flight hours and 9,393 total flight cycles. A dye penetrant inspection of the remaining seven latch pins in the lower sill was done with no defects found. This condition, if not corrected, could result in a forward or aft lower lobe cargo door opening and detaching during flight, and consequent rapid decompression of the airplane. Relevant Service Information We reviewed Boeing Alert Service Bulletin 747–53A2835, original, dated October 28, 2010. The service information describes procedures for repetitive general visual inspections for broken or missing latch pins of the lower sills of the forward and aft lower lobe cargo doors; repetitive detailed inspections of the replaced latch pins for broken or missing latch pins; and corrective actions if necessary. For Groups 1 and 2 airplanes, Configurations 1 and 2; and for Group 3 airplanes; the corrective actions include replacing any broken or missing latch pin, and the latch pins at the adjacent latch fitting locations, with new latch pins; and replacing any cracked latch pins with new latch pins. For Group 1 airplanes, Configurations 3 and 4, there are two options for corrective actions: • Replacing any broken or missing latch pin, and the latch pins at the adjacent latch fitting locations, with new latch pins (with identical part numbers); and replacing any cracked latch pins with new latch pins (with identical part numbers). • Modifying or replacing the latch pins and bearing plates; replacing any broken or missing latch pin, and the latch pins at the adjacent latch fitting locations, with new latch pins (with alternative part numbers); and replacing any cracked latch pins with new latch pins (with alternative part numbers). For airplanes on which all latch pins are replaced, the first repetitive inspection interval is within 6,000 flight cycles after replacement. For airplanes on which not all of the latch pins are replaced, the first repetitive inspection interval is 1,600 flight cycles after inspecting. For all airplanes, the repetitive interval for subsequent inspections is 1,600 flight cycles. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. Interim Action We consider this proposed AD interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. Costs of Compliance We estimate that this proposed AD affects 228 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection ......... 3 work-hours × $85 per hour = $255 per inspection cycle. VerDate Mar<15>2010 16:04 Aug 31, 2011 Jkt 223001 Parts cost PO 00000 Frm 00015 $0 Cost per product Cost on U.S. operators $255 per inspection cycle .............. Fmt 4702 Sfmt 4702 E:\FR\FM\01SEP1.SGM $58,140 per inspection cycle. 01SEP1 54407 Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules We estimate the following costs to do any necessary replacements/ modifications that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these actions: ON-CONDITION COSTS Action Labor cost Replacement of latch pins ................................................ Modification of latch fittings .............................................. 8 work-hours × $85 per hour = $680 ............................... 36 hours × $85 per work-hours = $3,060 ........................ emcdonald on DSK2BSOYB1PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect 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. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA– 2011–0915; Directorate Identifier 2011– NM–020–AD. Comments Due Date (a) We must receive comments by October 17, 2011. Affected ADs (b) None. Parts cost $0 0 Cost per product $680 3,060 Inspections (g) Before the accumulation of 6,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later: Do a general visual inspection for broken or missing latch pins of the lower sills of the forward and aft lower lobe cargo doors, and a detailed inspection for cracking of the latch pins, in accordance with paragraph 3.B., ‘‘Work Instructions,’’ of Boeing Alert Service Bulletin 747–53A2835, original, dated October 28, 2010. Repeat the inspections thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2835, original, dated October 28, 2010. Before further flight, do all applicable corrective actions, in accordance with paragraph 3.B., ‘‘Work Instructions,’’ of Boeing Alert Service Bulletin 747–53A2835, original, dated October 28, 2010. Special Flight Permits (h) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified (if the operator elects to do so), provided the cabin is not pressurized. List of Subjects in 14 CFR Part 39 Compliance Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes ODA that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (f) Comply with this AD within the compliance times specified, unless already done. Related Information (j) For more information about this AD, contact Nathan Weigand, Aerospace VerDate Mar<15>2010 16:04 Aug 31, 2011 Jkt 223001 Applicability (c) This AD applies to all The Boeing Company Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes; certificated in any category. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 53: Fuselage. Unsafe Condition (e) This AD was prompted by reports of fractured latch pins found in service; investigation revealed that the cracking and subsequent fracture were initiated by fatigue and propagated by a combination of fatigue and stress corrosion. We are issuing this AD to detect and correct fractured or broken latch pins, which could result in a forward or aft lower lobe cargo door opening and detaching during flight, and consequent rapid decompression of the airplane. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 E:\FR\FM\01SEP1.SGM 01SEP1 54408 Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: (425) 917–6428; fax: (425) 917–6590; e-mail: nathan.p.weigand@faa.gov. (k) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on August 25, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–22371 Filed 8–31–11; 8:45 am] will be received through October 26, 2011. You may submit comments, identified by docket ID number HHS– OPHS–2011–0005, by one of the following methods: • Federal eRulemaking Portal: https:// www.regulations.gov. Enter the above docket ID number in the ‘‘Enter Keyword or ID’’ field and click on ‘‘Search.’’ On the next web page, click on ‘‘Submit a Comment’’ action and follow the instructions. • Mail/Hand delivery/Courier [For paper, disk, or CD–ROM submissions] to: Jerry Menikoff, M.D., J.D., OHRP, 1101 Wootton Parkway, Suite 200, Rockville, MD 20852. Comments received, including any personal information, will be posted without change to https:// www.regulations.gov. Jerry Menikoff, M.D., J.D., Office for Human Research Protections (OHRP), Department of Health and Human Services, 1101 Wootton Parkway, Suite 200, Rockville, MD 20852; telephone: 240–453–6900 or 1–866–447–4777; facsimile: 301–402–2071; e-mail: jerry.menikoff@hhs.gov. FOR FURTHER INFORMATION CONTACT: Office of the Secretary 45 CFR Parts 46, 160, and 164 Food and Drug Administration The ANPRM was published in the Federal Register on July 26, 2011 (Volume 76, Number 143, page 44512) with a deadline for comments of September 26, 2011. The ANPRM requests comments on how current regulations for protecting human subjects who participate in research might be modernized and revised to be more effective and how to better protect human subjects who are involved in research, while facilitating valuable research and reducing burden, delay, and ambiguity for investigators. Since the ANPRM was published the Department has received requests to extend the comment period to allow sufficient time for a full review of the ANPRM. HHS and OSTP are committed to affording the public a meaningful opportunity to comment on the ANPRM and welcome comments. SUPPLEMENTARY INFORMATION: 21 CFR Parts 50 and 56 Human Subjects Research Protections: Enhancing Protections for Research Subjects and Reducing Burden, Delay, and Ambiguity for Investigators; Extension of Comment Period The Office of the Secretary, HHS, and the Food and Drug Administration, HHS. ACTION: Advance notice of proposed rulemaking; extension of comment period. AGENCIES: The Office of the Secretary of the Department of Health and Human Services (HHS) in coordination with the Office of Science and Technology Policy (OSTP) is extending the comment period for an advance notice of proposed rulemaking (ANPRM) requesting comment on how current regulations for protecting human subjects who participate in research might be modernized and revised to be more effective. That ANPRM was published in the Federal Register on July 26, 2011. DATES: The comment period for the proposed rule published July 26, 2011, at 76 FR 44512 is extended. Comments emcdonald on DSK2BSOYB1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 16:04 Aug 31, 2011 Jkt 223001 National Indian Gaming Commission ADDRESSES: BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES DEPARTMENT OF THE INTERIOR Dated: August 26, 2011. Kathleen Sebelius, Secretary. [FR Doc. 2011–22341 Filed 8–31–11; 8:45 am] BILLING CODE 4150–28–P PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 25 CFR Chapter III Regulatory Review Schedule National Indian Gaming Commission. ACTION: Notice of cancellation of consultation meeting. AGENCY: The purpose of this document is to cancel ten tribal consultations scheduled during November 2011, December 2011, January 2012, and February 2012 and to modify the dates for six tribal consultations scheduled during September 2011, October 2011 and November 2011. DATES: See SUPPLEMENTARY INFORMATION below for dates and locations of cancelled consultations. FOR FURTHER INFORMATION CONTACT: Lael Echo-Hawk, National Indian Gaming Commission, 1441 L Street, NW., Suite 9100, Washington, DC 20005. Telephone: 202–632–7003; e-mail: reg.review@nigc.gov. SUMMARY: On November 18, 2010, the National Indian Gaming Commission (NIGC) issued a Notice of Inquiry and Notice of Consultation advising the public that it was conducting a review of its regulations promulgated to implement 25 U.S.C. 2701–2721 of the Indian Gaming Regulatory Act (IGRA) and requesting public comment on the process for conducting the regulatory review. On April 4, 2011, after holding eight consultations and reviewing all comments, NIGC published a Notice of Regulatory Review Schedule in the Federal Register setting out consultation schedules and review processes. (76 FR 18457, April 4, 2011). The Commission’s regulatory review process established a tribal consultation schedule with a description of the regulation groups to be covered during consultation. Group 1 included a review of: (a) A Buy Indian Act regulation; (b) Part 523—Review and Approval of Existing Ordinances or Resolutions; (c) Part 514—Fees; (d) Part 559—Facility License Notifications, Renewals, and Submissions; and (e) Part 542—Minimum Internal Control Standards. Group 2 included a review of: (a) Part 573—Enforcement; and (b) Regulations concerning proceedings before the Commission, including: Parts 519—Service, Part 524—Appeals, Part 539—Appeals, and SUPPLEMENTARY INFORMATION: E:\FR\FM\01SEP1.SGM 01SEP1

Agencies

[Federal Register Volume 76, Number 170 (Thursday, September 1, 2011)]
[Proposed Rules]
[Pages 54405-54408]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-22371]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0915; Directorate Identifier 2011-NM-020-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD would require repetitive 
general visual inspections for broken or missing latch pins of the 
lower sills of the forward and aft lower lobe cargo doors; repetitive 
detailed inspections for cracking of the latch pins; and corrective 
actions if necessary. This proposed AD was prompted by reports of 
fractured latch pins found in service; investigation revealed that the 
cracking and subsequent fracture were initiated by fatigue and 
propagated by a combination of fatigue and stress corrosion. We are 
proposing this AD to detect and correct fractured or broken latch pins, 
which could result in a forward or aft lower lobe cargo door opening 
and detaching during flight, and consequent rapid decompression of the 
airplane.

DATES: We must receive comments on this proposed AD by October 17, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.

[[Page 54406]]

     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: (425) 917-
6428; fax: (425) 917-6590; e-mail: nathan.p.weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2011-0915; 
Directorate Identifier 2011-NM-020-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received reports of fractured latch pins found in service; 
investigation revealed that the cracking and subsequent fracture were 
initiated by fatigue and propagated by a combination of fatigue and 
stress corrosion. One operator reported a fractured latch pin of the 
lower sill of the aft lower lobe cargo door; the fracture initiated 
from a crack on the pin's internal diameter. Part of the pin was found 
on the ground during an airplane walk-around. The airplane had 
accumulated 75,495 total flight hours and 9,393 total flight cycles. A 
dye penetrant inspection of the remaining seven latch pins in the lower 
sill was done with no defects found. This condition, if not corrected, 
could result in a forward or aft lower lobe cargo door opening and 
detaching during flight, and consequent rapid decompression of the 
airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-53A2835, original, 
dated October 28, 2010. The service information describes procedures 
for repetitive general visual inspections for broken or missing latch 
pins of the lower sills of the forward and aft lower lobe cargo doors; 
repetitive detailed inspections of the replaced latch pins for broken 
or missing latch pins; and corrective actions if necessary.
    For Groups 1 and 2 airplanes, Configurations 1 and 2; and for Group 
3 airplanes; the corrective actions include replacing any broken or 
missing latch pin, and the latch pins at the adjacent latch fitting 
locations, with new latch pins; and replacing any cracked latch pins 
with new latch pins.
    For Group 1 airplanes, Configurations 3 and 4, there are two 
options for corrective actions:
     Replacing any broken or missing latch pin, and the latch 
pins at the adjacent latch fitting locations, with new latch pins (with 
identical part numbers); and replacing any cracked latch pins with new 
latch pins (with identical part numbers).
     Modifying or replacing the latch pins and bearing plates; 
replacing any broken or missing latch pin, and the latch pins at the 
adjacent latch fitting locations, with new latch pins (with alternative 
part numbers); and replacing any cracked latch pins with new latch pins 
(with alternative part numbers).
    For airplanes on which all latch pins are replaced, the first 
repetitive inspection interval is within 6,000 flight cycles after 
replacement. For airplanes on which not all of the latch pins are 
replaced, the first repetitive inspection interval is 1,600 flight 
cycles after inspecting. For all airplanes, the repetitive interval for 
subsequent inspections is 1,600 flight cycles.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously.

Interim Action

    We consider this proposed AD interim action. The manufacturer is 
currently developing a modification that will address the unsafe 
condition identified in this AD. Once this modification is developed, 
approved, and available, we might consider additional rulemaking.

Costs of Compliance

    We estimate that this proposed AD affects 228 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
           Action                  Labor cost         Parts cost     Cost per product     Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection.................  3 work-hours x $85 per           $0  $255 per inspection     $58,140 per inspection
                              hour = $255 per                      cycle.                  cycle.
                              inspection cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 54407]]

    We estimate the following costs to do any necessary replacements/
modifications that would be required based on the results of the 
proposed inspection. We have no way of determining the number of 
aircraft that might need these actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                       Cost per
                   Action                                    Labor cost                  Parts cost    product
----------------------------------------------------------------------------------------------------------------
Replacement of latch pins...................  8 work-hours x $85 per hour = $680......           $0         $680
Modification of latch fittings..............  36 hours x $85 per work-hours = $3,060..            0        3,060
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect 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.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

The Boeing Company: Docket No. FAA-2011-0915; Directorate Identifier 
2011-NM-020-AD.

Comments Due Date

    (a) We must receive comments by October 17, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all The Boeing Company Model 747-100, 
747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-
400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; 
certificated in any category.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 53: Fuselage.

Unsafe Condition

    (e) This AD was prompted by reports of fractured latch pins 
found in service; investigation revealed that the cracking and 
subsequent fracture were initiated by fatigue and propagated by a 
combination of fatigue and stress corrosion. We are issuing this AD 
to detect and correct fractured or broken latch pins, which could 
result in a forward or aft lower lobe cargo door opening and 
detaching during flight, and consequent rapid decompression of the 
airplane.

Compliance

    (f) Comply with this AD within the compliance times specified, 
unless already done.

Inspections

    (g) Before the accumulation of 6,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later: Do a general visual inspection for broken or 
missing latch pins of the lower sills of the forward and aft lower 
lobe cargo doors, and a detailed inspection for cracking of the 
latch pins, in accordance with paragraph 3.B., ``Work 
Instructions,'' of Boeing Alert Service Bulletin 747-53A2835, 
original, dated October 28, 2010. Repeat the inspections thereafter 
at the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2835, 
original, dated October 28, 2010. Before further flight, do all 
applicable corrective actions, in accordance with paragraph 3.B., 
``Work Instructions,'' of Boeing Alert Service Bulletin 747-53A2835, 
original, dated October 28, 2010.

Special Flight Permits

    (h) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the airplane can be modified (if the operator elects to do so), 
provided the cabin is not pressurized.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes ODA that has been authorized by the 
Manager, Seattle ACO, to make those findings. For a repair method to 
be approved, the repair must meet the certification basis of the 
airplane.

Related Information

    (j) For more information about this AD, contact Nathan Weigand, 
Aerospace

[[Page 54408]]

Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; phone: (425) 917-6428; fax: (425) 917-6590; e-mail: 
nathan.p.weigand@faa.gov.
    (k) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221.

    Issued in Renton, Washington, on August 25, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-22371 Filed 8-31-11; 8:45 am]
BILLING CODE 4910-13-P
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