Airworthiness Directives; The Boeing Company Airplanes, 42895-42898 [2013-17253]

Download as PDF Federal Register / Vol. 78, No. 138 / Thursday, July 18, 2013 / Proposed Rules 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. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 Bombardier, Inc.: Docket No. FAA–2013– 0548; Directorate Identifier 2013–NM– 008–AD. (a) Comments Due Date We must receive comments by September 3, 2013. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model BD–700–1A11 airplanes, certificated in any category, modified by FAA Supplemental Type Certificate (STC) ST02140NY, issued October 14, 2005. Internet: https://rgl.faa.gov/ VerDate Mar<15>2010 14:53 Jul 17, 2013 Jkt 229001 Regulatory_and_Guidance_Library/rgstc.nsf/ 0/6B8CF26D01F5E6DE862570C7006DCD7E? OpenDocument&Highlight=st02140ny. (d) Subject Air Transport Association (ATA) of America Code 35, Oxygen. (e) Reason This AD was prompted by a report that certain lanyards for the passenger oxygen masks are longer than the specified length, possibly leading to inactive oxygen masks in an emergency. We are issuing this AD to detect and correct lanyards of incorrect length, which might not activate the flow of oxygen in an emergency, resulting in injury to passengers. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Replacement Within 750 flight hours or 15 months after the effective date of this AD, whichever occurs first: Replace lanyards having part numbers (PN) B431564–503 and –505 for all passenger oxygen dispensing units, with lanyards having PN B431564–507, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 700–1A11–35–009, dated October 22, 2012. (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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. The AMOC approval letter must specifically reference this AD. (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. (i) Related Information (1) Refer to Canadian Airworthiness Directive CF–2012–31, dated December 7, 2012, for related information. (2) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 42895 Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@aero.bombardier.com; Internet https:// www.bombardier.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on July 5, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–17255 Filed 7–17–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0547; Directorate Identifier 2013–NM–028–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 727–200 and 727–200F series airplanes. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would require a one-time inspection for cracking of the pressure floor of both main wheel wells, and related investigative and corrective actions if necessary; and would require modifying the pressure floor of both main wheel wells. We are proposing this AD to prevent fatigue cracking in the pressure floor of the main wheel wells, which could lead to rapid loss of cabin pressurization. SUMMARY: We must receive comments on this proposed AD by September 3, 2013. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, DATES: E:\FR\FM\18JYP1.SGM 18JYP1 42896 Federal Register / Vol. 78, No. 138 / Thursday, July 18, 2013 / Proposed Rules 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; 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, WA. 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: Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712–4137; phone: 562–627–5324; fax: 562–627–5210; email: Galib.Abumeri@faa.gov. SUPPLEMENTARY INFORMATION: pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 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– 2013–0547; Directorate Identifier 2013– NM–028–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 VerDate Mar<15>2010 14:53 Jul 17, 2013 Jkt 229001 substantive verbal contact we receive about this proposed AD. Discussion As described in FAA Advisory Circular 120–104 (https://www.faa.gov/ documentLibrary/media/ Advisory_Circular/120-104.pdf), several programs have been developed to support initiatives that will ensure the continued airworthiness of aging airplane structure. The last element of those initiatives is the requirement to establish a LOV of the engineering data that support the structural maintenance program under 14 CFR 26.21. This AD is the result of an assessment of the previously established programs by Boeing during the process of establishing the LOV for Boeing Model 727 series airplanes. The action specified in this proposed AD is necessary to complete certain programs to ensure the continued airworthiness of aging airplane structure and to support an airplane reaching its LOV. We have received reports of cracks in the pressure floor of the main landing gear (MLG) wheel wells. Three operators reported cracks from 25 to 48 inches long, resulting in rapid decompression of the airplane. Twenty-four operators reported 67 airplanes with cracks up to two inches located in the reinforcing beads on both sides of the frame. This fatigue cracking, if not corrected, could result in rapid loss of cabin pressurization. Relevant Service Information We reviewed Boeing Service Bulletin 727–53A0124, Revision 3, dated November 30, 1989. For information on the procedures and compliance times, see this service information at https:// www.regulations.gov by searching for Docket No. FAA–2013–0547. ‘‘Preventive Modification,’’ of the Accomplishment Instructions of the service information described previously. The phrase ‘‘related investigative actions’’ is used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that: (1) Are related to the primary actions, and (2) are actions that further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. In addition, the phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between the Proposed AD and the Service Information Prior to accomplishing the preventive modification, this proposed AD would require a one-time inspection of the pressure floor for cracks in both the right and left main wheel wells, and corrective actions if necessary, in lieu of the repetitive inspections specified in Boeing Service Bulletin 727–53A0124, Revision 3, dated November 30, 1989. The repetitive inspections are addressed by AD 91–22–08, Amendment 39–8068 (56 FR 57233, November 8, 1991). Additionally, the applicability of this proposed AD is different than the effectivity described in Boeing Service Bulletin 727–53A0124, Revision 3, dated November 30, 1989. 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 the same type design. Explanation of Compliance Time The compliance time for the modification specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Proposed AD Requirements This proposed AD would require a one-time eddy current inspection, penetrant inspection, or detailed inspection for cracking of the pressure floor of both main wheel wells as described in Part I, ‘‘Inspection,’’ of the Accomplishment Instructions of the service information described previously, and related investigative and corrective actions if necessary; and would also require accomplishing the modification specified in Part III, Related Rulemaking AD 90–06–09, Amendment 39–6488 (55 FR 8370, March 7, 1990), requires accomplishing the preventive modification specified in Boeing Alert Service Bulletin 727–53A0124, Revision 2, dated May 2, 1975, for airplane line numbers 1 through 1102 inclusive. AD 91–22–08, Amendment 39–8068 (56 FR 57233, November 8, 1991), requires compliance with the inspection and repair, if necessary specified in Boeing Service Bulletin 727–53A0124, Revision PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\18JYP1.SGM 18JYP1 Federal Register / Vol. 78, No. 138 / Thursday, July 18, 2013 / Proposed Rules 3, dated November 30, 1989, for airplane line numbers 1 through 1832 inclusive, but does not require the preventive modification. Costs of Compliance We estimate that this proposed AD affects 94 airplanes of U.S. registry. 42897 We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost Inspection and Modification .... 222 work-hours × $85 per hour = $18,870 ............................ We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Authority for This Rulemaking The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 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. pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 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. VerDate Mar<15>2010 14:53 Jul 17, 2013 Jkt 229001 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– 2013–0547; Directorate Identifier 2013– NM–028–AD. (a) Comments Due Date We must receive comments by September 3, 2013. (b) Affected ADs This AD affects AD 91–22–08, Amendment 39–8068 (56 FR 57233, November 8, 1991). (c) Applicability This AD applies to The Boeing Company Model 727–200 and 727–200F series airplanes, certificated in any category, lines numbers 1103 and subsequent. $2,906 Cost per product $21,776 Cost on U.S. operators $2,046,944 (g) Inspection Before the accumulation of 60,000 total flight cycles, or within 24 months after the effective date of this AD, whichever occurs later: Do a one-time detailed inspection for cracking of the pressure floor of both main wheel wells, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727–53A0124, Revision 3, dated November 30, 1989, except as specified in paragraph (h) of this AD. If any indication of distress is found (such as cracking or flaked paint): Before further flight do an eddy current inspection or penetrant inspection for cracking of the pressure floor of both main wheel wells, and do all applicable related investigative and corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 727–53A0124, Revision 3, dated November 30, 1989. Do all applicable related investigative and corrective actions before further flight. (h) Exception to Service Information Where Boeing Service Bulletin 727– 53A0124, Revision 3, dated November 30, 1989, specifies a close visual inspection, this AD requires a detailed inspection, which is an intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to prevent fatigue cracking in the pressure floor of the main wheel wells, which could lead to rapid loss of cabin pressurization. (i) Preventive Modification Before further flight after accomplishing the actions required by paragraph (g) of this AD: Do a preventive modification of the pressure floor of both main wheel wells, in accordance with Part III of the Accomplishment Instructions of Boeing Service Bulletin 727–53A0124, Revision 3, dated November 30, 1989. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 727–53A0124, Revision 2, dated May 2, 1975. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (k) Termination of Certain Actions in AD 91–22–08, Amendment 39–8068 (56 FR 57233, November 8, 1991) Accomplishment of the preventative modification required by paragraph (i) of this E:\FR\FM\18JYP1.SGM 18JYP1 42898 Federal Register / Vol. 78, No. 138 / Thursday, July 18, 2013 / Proposed Rules AD terminates the repetitive inspection requirement required by AD 91–22–08, Amendment 39–8068 (56 FR 57233, November 8, 1991) for airplanes with line number 1103 and subsequent. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration (l) Alternative Methods of Compliance (AMOCs) [Docket No. FAA–2013–0624; Directorate Identifier 2013–NM–071–AD] (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 emailed 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 Organization Designation Authorization (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, and the approval must specifically refer to this AD. RIN 2120–AA64 You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 (m) Related Information pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 (1) For more information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712–4137; phone: 562–627–5324; fax: 562– 627–5210; email: Galib.Abumeri@faa.gov. (2) 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; 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, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on July 5, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–17253 Filed 7–17–13; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 14:53 Jul 17, 2013 Jkt 229001 Airworthiness Directives; ATR–GIE ´ Avions de Transport Regional Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain ´ ATR–GIE Avions de Transport Regional Model ATR72–101, –201, –102, –202, –211, –212, and –212A airplanes. This proposed AD was prompted by reports of airplane incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation that resulted in engine flameouts. This proposed AD would require installing a fuel quantity indicator (FQI) equipped with a locking adaptor on the electrical connector. We are proposing this AD to prevent an engine flame-out, which could result in reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by September 3, 2013. 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. • 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact ATR–GIE ´ ´ Avions de Transport Regional, 1, Allee Pierre Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; email continued.airworthiness@atr.fr; Internet https://www.aerochain.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2013–0624; Directorate Identifier 2013–NM–071–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 based on 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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0047, dated March 4, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Large aeroplane incidents and accidents have occurred because of fuel tank low level situations, or because of fuel starvation, resulting in one or several engine(s) flameout. The results of the investigation into an ATR 72 accident in August 2005 have shown that overruling standard operational procedures and maintenance practices have led to this kind of occurrence. E:\FR\FM\18JYP1.SGM 18JYP1

Agencies

[Federal Register Volume 78, Number 138 (Thursday, July 18, 2013)]
[Proposed Rules]
[Pages 42895-42898]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-17253]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0547; Directorate Identifier 2013-NM-028-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 727-200 and 727-200F series airplanes. 
This proposed AD is intended to complete certain mandated programs 
intended to support the airplane reaching its limit of validity (LOV) 
of the engineering data that support the established structural 
maintenance program. This proposed AD would require a one-time 
inspection for cracking of the pressure floor of both main wheel wells, 
and related investigative and corrective actions if necessary; and 
would require modifying the pressure floor of both main wheel wells. We 
are proposing this AD to prevent fatigue cracking in the pressure floor 
of the main wheel wells, which could lead to rapid loss of cabin 
pressurization.

DATES: We must receive comments on this proposed AD by September 3, 
2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations,

[[Page 42896]]

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; 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, WA. 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: Galib Abumeri, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712-4137; 
phone: 562-627-5324; fax: 562-627-5210; email: Galib.Abumeri@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-2013-0547; 
Directorate Identifier 2013-NM-028-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

    As described in FAA Advisory Circular 120-104 (https://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a LOV of the 
engineering data that support the structural maintenance program under 
14 CFR 26.21. This AD is the result of an assessment of the previously 
established programs by Boeing during the process of establishing the 
LOV for Boeing Model 727 series airplanes. The action specified in this 
proposed AD is necessary to complete certain programs to ensure the 
continued airworthiness of aging airplane structure and to support an 
airplane reaching its LOV.
    We have received reports of cracks in the pressure floor of the 
main landing gear (MLG) wheel wells. Three operators reported cracks 
from 25 to 48 inches long, resulting in rapid decompression of the 
airplane. Twenty-four operators reported 67 airplanes with cracks up to 
two inches located in the reinforcing beads on both sides of the frame. 
This fatigue cracking, if not corrected, could result in rapid loss of 
cabin pressurization.

Relevant Service Information

    We reviewed Boeing Service Bulletin 727-53A0124, Revision 3, dated 
November 30, 1989. For information on the procedures and compliance 
times, see this service information at https://www.regulations.gov by 
searching for Docket No. FAA-2013-0547.

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 the same type design.

Proposed AD Requirements

    This proposed AD would require a one-time eddy current inspection, 
penetrant inspection, or detailed inspection for cracking of the 
pressure floor of both main wheel wells as described in Part I, 
``Inspection,'' of the Accomplishment Instructions of the service 
information described previously, and related investigative and 
corrective actions if necessary; and would also require accomplishing 
the modification specified in Part III, ``Preventive Modification,'' of 
the Accomplishment Instructions of the service information described 
previously.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that: (1) Are related to the primary actions, and (2) are actions that 
further investigate the nature of any condition found. Related 
investigative actions in an AD could include, for example, inspections.
    In addition, the phrase ``corrective actions'' is used in this 
proposed AD. ``Corrective actions'' are actions that correct or address 
any condition found. Corrective actions in an AD could include, for 
example, repairs.

Differences Between the Proposed AD and the Service Information

    Prior to accomplishing the preventive modification, this proposed 
AD would require a one-time inspection of the pressure floor for cracks 
in both the right and left main wheel wells, and corrective actions if 
necessary, in lieu of the repetitive inspections specified in Boeing 
Service Bulletin 727-53A0124, Revision 3, dated November 30, 1989. The 
repetitive inspections are addressed by AD 91-22-08, Amendment 39-8068 
(56 FR 57233, November 8, 1991). Additionally, the applicability of 
this proposed AD is different than the effectivity described in Boeing 
Service Bulletin 727-53A0124, Revision 3, dated November 30, 1989.

Explanation of Compliance Time

    The compliance time for the modification specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is modified before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

Related Rulemaking

    AD 90-06-09, Amendment 39-6488 (55 FR 8370, March 7, 1990), 
requires accomplishing the preventive modification specified in Boeing 
Alert Service Bulletin 727-53A0124, Revision 2, dated May 2, 1975, for 
airplane line numbers 1 through 1102 inclusive. AD 91-22-08, Amendment 
39-8068 (56 FR 57233, November 8, 1991), requires compliance with the 
inspection and repair, if necessary specified in Boeing Service 
Bulletin 727-53A0124, Revision

[[Page 42897]]

3, dated November 30, 1989, for airplane line numbers 1 through 1832 
inclusive, but does not require the preventive modification.

Costs of Compliance

    We estimate that this proposed AD affects 94 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection and Modification........  222 work[dash]hours x $85            $2,906         $21,776      $2,046,944
                                      per hour = $18,870.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2013-0547; Directorate Identifier 
2013-NM-028-AD.

(a) Comments Due Date

    We must receive comments by September 3, 2013.

(b) Affected ADs

    This AD affects AD 91-22-08, Amendment 39-8068 (56 FR 57233, 
November 8, 1991).

(c) Applicability

    This AD applies to The Boeing Company Model 727-200 and 727-200F 
series airplanes, certificated in any category, lines numbers 1103 
and subsequent.

(d) Subject

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

(e) Unsafe Condition

    This AD is intended to complete certain mandated programs 
intended to support the airplane reaching its limit of validity 
(LOV) of the engineering data that support the established 
structural maintenance program. We are issuing this AD to prevent 
fatigue cracking in the pressure floor of the main wheel wells, 
which could lead to rapid loss of cabin pressurization.

(f) Compliance

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

(g) Inspection

    Before the accumulation of 60,000 total flight cycles, or within 
24 months after the effective date of this AD, whichever occurs 
later: Do a one-time detailed inspection for cracking of the 
pressure floor of both main wheel wells, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 727-53A0124, 
Revision 3, dated November 30, 1989, except as specified in 
paragraph (h) of this AD. If any indication of distress is found 
(such as cracking or flaked paint): Before further flight do an eddy 
current inspection or penetrant inspection for cracking of the 
pressure floor of both main wheel wells, and do all applicable 
related investigative and corrective actions, by accomplishing all 
the actions specified in the Accomplishment Instructions of Boeing 
Service Bulletin 727-53A0124, Revision 3, dated November 30, 1989. 
Do all applicable related investigative and corrective actions 
before further flight.

(h) Exception to Service Information

    Where Boeing Service Bulletin 727-53A0124, Revision 3, dated 
November 30, 1989, specifies a close visual inspection, this AD 
requires a detailed inspection, which is an intensive examination of 
a specific item, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at an intensity 
deemed appropriate. Inspection aids such as mirror, magnifying 
lenses, etc., may be necessary. Surface cleaning and elaborate 
procedures may be required.

(i) Preventive Modification

    Before further flight after accomplishing the actions required 
by paragraph (g) of this AD: Do a preventive modification of the 
pressure floor of both main wheel wells, in accordance with Part III 
of the Accomplishment Instructions of Boeing Service Bulletin 727-
53A0124, Revision 3, dated November 30, 1989.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(i) of this AD, if those actions were performed before the effective 
date of this AD using Boeing Alert Service Bulletin 727-53A0124, 
Revision 2, dated May 2, 1975.

(k) Termination of Certain Actions in AD 91-22-08, Amendment 39-8068 
(56 FR 57233, November 8, 1991)

    Accomplishment of the preventative modification required by 
paragraph (i) of this

[[Page 42898]]

AD terminates the repetitive inspection requirement required by AD 
91-22-08, Amendment 39-8068 (56 FR 57233, November 8, 1991) for 
airplanes with line number 1103 and subsequent.

(l) Alternative Methods of Compliance (AMOCs)

    (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 emailed 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 Organization Designation Authorization 
(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, and the approval must 
specifically refer to this AD.

(m) Related Information

    (1) For more information about this AD, contact Galib Abumeri, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Blvd., Suite 100, 
Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-5210; 
email: Galib.Abumeri@faa.gov.
    (2) 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; 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, WA. For information on the availability of 
this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 5, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-17253 Filed 7-17-13; 8:45 am]
BILLING CODE 4910-13-P
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