Airworthiness Directives; The Boeing Company Airplanes, 28023-28026 [2017-12612]

Download as PDF Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules Issue 19, dated March 23, 2012; ‘‘Variation to Issue 19 of ALI Document (referenced in ALS Part 2) Damage Tolerant Airworthiness Limitation Items (DT ALI),’’ variation reference 0GVLG120018/C0S, dated October 24, 2012; and ‘‘Variation to Issue 19 of ALI Document (referenced in ALS Part 2) Damage Tolerant Airworthiness Limitation Items (DT ALI),’’ 0GVLG130002/C01, dated March 26, 2013; are at the times specified in Airbus Document AI/SE–M4/95A.0089/97, ‘‘A330 Airworthiness Limitation Items,’’ Issue 19, dated March 23, 2012; ‘‘Variation to Issue 19 of ALI Document (referenced in ALS Part 2) Damage Tolerant Airworthiness Limitation Items (DT ALI),’’ variation ref. 0GVLG120018/C0S, dated October 24, 2012; and ‘‘Variation to Issue 19 of ALI Document (referenced in ALS Part 2) Damage Tolerant Airworthiness Limitation Items (DT ALI),’’ variation ref. 0GVLG130002/C01, dated March 26, 2013; or within 3 months after October 8, 2014 (the effective date of AD 2014–17–06), whichever occurs later. later. Accomplishing the revision specified in this paragraph terminates the requirements of paragraph (g) of this AD and the provision specified in paragraph (h) of this AD. (1) Airbus A330 Airworthiness Limitations Section (ALS) Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 01, issue 02, dated November 30, 2015. (2) Airbus 330 ALS Part 2, DT-ALI, Variation 1.1, dated December 15, 2015. (3) Airbus 330 ALS Part 2, DT-ALI, Variation 1.2, dated May 27, 2016. (h) Retained Provision: Optional Compliance, With a New Terminating Action This paragraph restates the provision in paragraph (j) of AD 2014–17–06, with a new terminating action. Compliance with tasks 533021–02–01, 533021–02–02, and 533021– 02–03, specified in ‘‘Variation to Issue 19 of ALI Document (referenced in ALS Part 2) Damage Tolerant Airworthiness Limitation Items (DT ALI),’’ variation ref. 0GVLG120022/C0S, dated December 21, 2012, may be used as a method of compliance to tasks 533021–01–01, 533021– 01–02, 533021–01–03 specified in Section 2.2.1 and 2.2.2 of Section 2, ‘‘Airworthiness Limitations,’’ of Airbus Document AI/SE M4/ 95A.0089/97, ‘‘A330 Airworthiness Limitation Items,’’ Issue 19, dated March 23, 2012. Accomplishing the revision required by paragraph (j) of this AD terminates the provision specified in this paragraph. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS (i) Retained Requirement: No Alternative Intervals or Limits, With a New Exception This paragraph restates the requirements of paragraph (k) of AD 2014–17–06, with a new exception. Except as provided by paragraph (h) of this AD and as required by paragraph (j) of this AD, after the maintenance or inspection program, as applicable, has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) under the provisions of paragraph (l)(1) of this AD. (j) New Requirement: Maintenance or Inspection Program Revision Within 3 months after the effective date of this AD: Revise the maintenance or inspection program, as applicable, by incorporating the service information specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD. The initial compliance times for the actions specified in the service information referenced in paragraphs (j)(1), (j)(2), and (j)(3) of this AD are the times specified in the applicable service information, or within 3 months after the effective date of this AD, whichever occurs VerDate Sep<11>2014 17:28 Jun 19, 2017 Jkt 241001 (k) New Requirement: No Alternative Actions or Intervals After the maintenance or inspection program, as applicable, has been revised, as required by paragraph (j) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (l)(1) of this AD. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0152, dated July 27, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2017–0561. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 28023 (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this 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 June 9, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–12614 Filed 6–19–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0559; Directorate Identifier 2017–NM–013–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 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 airplanes. This proposed AD was prompted by a report of damage found at the lower trailing edge panels of the left wing and a broken fuse pin of the landing gear beam end fitting. This proposed AD would require repetitive replacement or inspection of certain fuse pins, and applicable on-condition actions. We are proposing this AD to address the unsafe condition on these products. SUMMARY: We must receive comments on this proposed AD by August 4, 2017. 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 http://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 DATES: E:\FR\FM\20JNP1.SGM 20JNP1 28024 Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules 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 NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; Internet https:// www.myboeingfleet.com. You may view this 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0559. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0559; 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: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6432; fax: 425– 917–6590; email: bill.ashforth@faa.gov. SUPPLEMENTARY INFORMATION: 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–2017–0559; Directorate Identifier 2017–NM–013–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 http:// 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 a report indicating damage to the lower trailing edge panels of the left wing of a 747–400 airplane. Further inspection revealed that the left wing fuse pin of the landing gear beam end fitting had broken into two pieces. The airplane had 17,879 total flight cycles and 102,793 total flight hours at the time of the failure. Boeing has done an analysis and determined that the fuse pin broke as a result of fatigue. Fatigue cracking of the fuse pin, if not corrected, could result in a broken fuse pin. A broken fuse pin will not support the wing landing gear beam, causing damage to the surrounding structure, including flight control cables and hydraulic systems, which could result in loss of controllability of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747–57A2360, dated January 20, 2017. The service information describes procedures for repetitive replacement or inspection of certain fuse pins, and applicable on-condition actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. 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 accomplishment of the actions identified as ‘‘RC’’ (required for compliance) in the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2360, dated January 20, 2017, described previously, except for any differences between this proposed AD and the service information that are identified in the regulatory text of this proposed AD. Although the crack reports that prompted this proposed AD were found only on the left wing, this proposed AD would require actions on both wings. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0559. Costs of Compliance We estimate that this proposed AD affects 158 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Cost per product Labor cost Fuse pin replacement 1 ........................... 46 work-hours × $85 per hour = $3,910 per replacement cycle. $15,150 Magnetic particle inspection 1 .................. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS Action 48 work-hours × $85 per hour = $4,080 per inspection cycle. 10 work-hours × $85 per hour = $850 per inspection cycle. 0 Surface inspection 1 ................................. 1 Operators $19,060 per replacement cycle. Up to $3,011,480 per replacement cycle. Up to $644,640 per inspection cycle. Up to $134,300 per inspection cycle. 0 $4,080 per inspection cycle. $850 per inspection cycle. may choose which action they want to use. We estimate the following costs to do any necessary replacements that would VerDate Sep<11>2014 Cost on U.S. operators Parts cost 17:28 Jun 19, 2017 Jkt 241001 be required based on the results of the proposed inspection. We have no way of PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 determining the number of aircraft that might need these replacements: E:\FR\FM\20JNP1.SGM 20JNP1 Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules 28025 ON-CONDITION COSTS Action Labor cost Parts cost Fuse pin replacement ......................................... 46 work-hours × $85 per hour = $3,910 .......... Up to $15,150 ............. 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. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS 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, VerDate Sep<11>2014 17:28 Jun 19, 2017 Jkt 241001 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– 2017–0559; Directorate Identifier 2017– NM–013–AD. (a) Comments Due Date We must receive comments by August 4, 2017. (b) Affected ADs None. (c) Applicability 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 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a report of damage found at the lower trailing edge panels of the left wing and a broken fuse pin of the landing gear beam end fitting. We are issuing this AD to detect and correct cracking in the fuse pin of the wing landing gear beam end fitting. A broken fuse pin will not support the wing landing gear beam, causing damage to the surrounding structure, including flight control cables and hydraulic systems, which could result in loss of controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions Required for Compliance Except as required by paragraph (h) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–57A2360, dated January 20, 2017, do all applicable actions identified as required for compliance (‘‘RC’’) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2360, dated January 20, 2017. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Cost per product Up to $19,060. (h) Exception to the Service Information Where Boeing Alert Service Bulletin 747– 57A2360, dated January 20, 2017, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), Transport Airplane Directorate, 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 paragraph (j)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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, modification, or alteration 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. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, E:\FR\FM\20JNP1.SGM 20JNP1 28026 Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425– 917–6590; email: bill.ashforth@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; Internet https:// www.myboeingfleet.com. You may view this 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 June 9, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–12612 Filed 6–19–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0608; Directorate Identifier 2017–CE–017–AD] RIN 2120–AA64 Airworthiness Directives; Textron Aviation Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Textron Aviation Inc. Model 390 airplanes (type certificate previously held by Beechcraft Corporation). This proposed AD was prompted by reports of hydraulic fluid loss from the engine driven pumps (EDPs) on three different airplanes. This proposed AD would require an inspection to determine if an affected EDP is installed with replacement as necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by August 4, 2017. 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 http://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 asabaliauskas on DSKBBXCHB2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:28 Jun 19, 2017 Jkt 241001 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 NPRM, contact Textron Aviation Inc., Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; email: premier@txtav.com; Internet: www.txtavsupport.com. You may view this 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0608; 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 NPRM, 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: Paul C. DeVore, Aerospace Engineer, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4142; fax: (316) 946–4107, email: paul.devore@faa.gov or Wichita-COS@ 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– 2017–0608; Directorate Identifier 2017– CE–017–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Discussion We received reports of hydraulic fluid loss from the engine driven pumps (EDPs) on three different Textron Aviation Inc. Model 390 airplanes. In one incident, the airplane exited the runway at a high speed, resulting in extensive damage to the airplane. One manufacturing lot of EDPs has excessive pitting in the aluminum port caps that could cause multiple-origin fatigue cracking of the port caps. Flammable hydraulic fluid could leak into the engine compartment, and the leaking could also cause loss of all normal hydraulic functions, including normal anti-skid braking, ground spoilers, speedbrakes, and normal landing gear extension. This condition, if not corrected, could result in loss of normal hydraulic functions, which could lead to a high-speed runway overrun and/or an in-flight fire. Related Service Information Under 1 CFR Part 51 We reviewed Parker Service Bulletin 66179–29–486, dated August 4, 2016, which identifies the affected serial number EDPs. We also reviewed Beechcraft Mandatory Service Bulletin SB 29–4161, dated November 18, 2016, which describes procedures for determining if an affected serial number EDP is installed and procedures for replacing the EDP if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. 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 accomplishing the actions specified in the service information described previously except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ Differences Between This Proposed AD and the Service Information The service information specifies a compliance time of 200 hours time-inservice (TIS) or 12 months, whichever occurs first. This proposed AD would require a compliance of 100 hours TIS to reduce the possibility of another incident due to a cracked EDP. We removed the 12 month calendar time from the compliance time because we E:\FR\FM\20JNP1.SGM 20JNP1

Agencies

[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Proposed Rules]
[Pages 28023-28026]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12612]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0559; Directorate Identifier 2017-NM-013-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 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 airplanes. This proposed AD was prompted by a report of damage 
found at the lower trailing edge panels of the left wing and a broken 
fuse pin of the landing gear beam end fitting. This proposed AD would 
require repetitive replacement or inspection of certain fuse pins, and 
applicable on-condition actions. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by August 4, 2017.

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 http://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

[[Page 28024]]

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 NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may 
view this 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. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0559.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0559; 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: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION: 

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-2017-0559; 
Directorate Identifier 2017-NM-013-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 http://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 a report indicating damage to the lower trailing 
edge panels of the left wing of a 747-400 airplane. Further inspection 
revealed that the left wing fuse pin of the landing gear beam end 
fitting had broken into two pieces. The airplane had 17,879 total 
flight cycles and 102,793 total flight hours at the time of the 
failure. Boeing has done an analysis and determined that the fuse pin 
broke as a result of fatigue. Fatigue cracking of the fuse pin, if not 
corrected, could result in a broken fuse pin. A broken fuse pin will 
not support the wing landing gear beam, causing damage to the 
surrounding structure, including flight control cables and hydraulic 
systems, which could result in loss of controllability of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-57A2360, dated 
January 20, 2017. The service information describes procedures for 
repetitive replacement or inspection of certain fuse pins, and 
applicable on-condition actions. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

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 accomplishment of the actions 
identified as ``RC'' (required for compliance) in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2360, dated 
January 20, 2017, described previously, except for any differences 
between this proposed AD and the service information that are 
identified in the regulatory text of this proposed AD. Although the 
crack reports that prompted this proposed AD were found only on the 
left wing, this proposed AD would require actions on both wings.
    For information on the procedures and compliance times, see this 
service information at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2017-0559.

Costs of Compliance

    We estimate that this proposed AD affects 158 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
----------------------------------------------------------------------------------------------------------------
Fuse pin replacement \1\.....  46 work-hours x $85           $15,150  $19,060 per       Up to $3,011,480 per
                                per hour = $3,910                      replacement       replacement cycle.
                                per replacement                        cycle.
                                cycle.
Magnetic particle inspection   48 work-hours x $85                 0  $4,080 per        Up to $644,640 per
 \1\.                           per hour = $4,080                      inspection        inspection cycle.
                                per inspection cycle.                  cycle.
Surface inspection \1\.......  10 work-hours x $85                 0  $850 per          Up to $134,300 per
                                per hour = $850 per                    inspection        inspection cycle.
                                inspection cycle.                      cycle.
----------------------------------------------------------------------------------------------------------------
\1\ Operators may choose which action they want to use.

    We estimate the following costs to do any necessary replacements 
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 replacements:

[[Page 28025]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                       Labor cost              Parts cost             Cost per product
----------------------------------------------------------------------------------------------------------------
Fuse pin replacement.............  46 work-hours x $85 per    Up to $15,150.......  Up to $19,060.
                                    hour = $3,910.
----------------------------------------------------------------------------------------------------------------

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-2017-0559; Directorate Identifier 
2017-NM-013-AD.

(a) Comments Due Date

    We must receive comments by August 4, 2017.

(b) Affected ADs

    None.

 (c) Applicability

    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 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of damage found at the lower 
trailing edge panels of the left wing and a broken fuse pin of the 
landing gear beam end fitting. We are issuing this AD to detect and 
correct cracking in the fuse pin of the wing landing gear beam end 
fitting. A broken fuse pin will not support the wing landing gear 
beam, causing damage to the surrounding structure, including flight 
control cables and hydraulic systems, which could result in loss of 
controllability of the airplane.

(f) Compliance

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

(g) Actions Required for Compliance

    Except as required by paragraph (h) of this AD: At the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-57A2360, dated January 20, 2017, 
do all applicable actions identified as required for compliance 
(``RC'') in, and in accordance with, the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2360, dated January 20, 
2017.

(h) Exception to the Service Information

    Where Boeing Alert Service Bulletin 747-57A2360, dated January 
20, 2017, specifies a compliance time ``after the original issue 
date of this service bulletin,'' this AD requires compliance within 
the specified compliance time after the effective date of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
Transport Airplane Directorate, 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 paragraph 
(j)(1) 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, modification, or alteration 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. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(i)(4)(i) and (i)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(j) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer,

[[Page 28026]]

Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6432; fax: 425-917-6590; 
email: bill.ashforth@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this 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 June 9, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-12612 Filed 6-19-17; 8:45 am]
 BILLING CODE 4910-13-P