82 FR 1262 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 3 (January 5, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 3 (January 5, 2017)
| Page Range | 1262-1265 | |
| FR Document | 2016-31619 |
[Federal Register Volume 82, Number 3 (Thursday, January 5, 2017)] [Proposed Rules] [Pages 1262-1265] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-31619] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9566; Directorate Identifier 2016-NM-191-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 757-200, -200PF, and -200CB series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage circumferential splice plates are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive low frequency eddy current (LFEC) inspections for cracks of certain circumferential splice plates, and repairs if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 21, 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 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 [[Page 1263]] and locating Docket No. FAA-2016-9566. 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-2016- 9566; 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: Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected]. 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-2016-9566; Directorate Identifier 2016-NM-191-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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. We have received a report indicating that the fuselage circumferential splice plates along the center fastener rows, forward and aft of station 900 and station 1180 splice centerlines, are susceptible to WFD. There have been no reports of cracking on airplanes in service. Inspections will mitigate a safety issue, allowing continued operation to the limit of validity. This condition, if not corrected, could result in failure of a principle structural element, which could adversely impact the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 757-53A0105, dated June 10, 2016. The service information describes procedures for repetitive LFEC inspections and repairs of the circumferential splice plates at station 900 and station 1180, from stringer S-6L to stringer S-6R, for any cracks. 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.'' 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-2016-9566. The phrase ``corrective actions'' is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 757-53A0105, dated June 10, 2016, specifies to contact the manufacturer for certain instructions, but this proposed AD would require using repair methods, modification deviations, and alteration deviations in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 634 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: [[Page 1264]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Parts Cost on U.S. Action Labor cost cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- LFEC inspection................... 6 work-hours x $85 $0 $510 per inspection $323,340 per per hour = $510 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- 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-2016-9566; Directorate Identifier 2016-NM-191-AD. (a) Comments Due Date We must receive comments by February 21, 2017. (b) Affected ADs This AD affects AD 2006-11-11, Amendment 39-14615 (71 FR 30278, May 26, 2006) (``AD 2006-11-11''). (c) Applicability This AD applies to all The Boeing Company Model 757-200, -200PF, and -200CB series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage circumferential splice plates along the center fastener rows, forward and aft of station 900 and station 1180 splice centerlines, are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct any such cracks, which could lead to the failure of a principal structural element and consequently adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Low Frequency Eddy Current (LFEC) Inspections and Corrective Actions At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 757-53A0105, dated June 10, 2016, except as required by paragraph (h)(1) of this AD: Do an LFEC inspection for cracking of the circumferential splice plates at station 900 and station 1180, from stringer S-6L to stringer S- 6R, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757- 53A0105, dated June 10, 2016, except as required by paragraph (h)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 757-53A0105, dated June 10, 2016. Accomplishing these inspections terminates the requirements of paragraph (h) of AD 2006- 11-11 for the inspections of structurally significant item (SSI) 53- 40-05, circumferential skin splice body station BS900 stringer S-6L to stringer S-6R and circumferential skin splice body station BS1180 stringer S-6L to stringer S-6R, as specified in Section 9 of Boeing Maintenance Planning Data (MPD) Document D622N001-9, May 2003 or June 2005 revisions. All other provisions of AD 2006-11-11 remain fully applicable and must be complied with. (h) Service Information Exceptions (1) Where Boeing Alert Service Bulletin 757-53A0105, dated June 10, 2016, 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. (2) Where Boeing Alert Service Bulletin 757-53A0105, dated June 10, 2016, specifies to contact Boeing for repair instructions, and specifies that action as Required for Compliance (RC), this AD requires repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 paragraph (j)(1) of this AD. Information may be emailed to: [email protected]. (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. [[Page 1265]] (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, Los Angeles 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) Except as required by paragraph (h) of this AD: For service information that contains steps that are labeled as 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 Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5348; fax: 562-627-5210; email: [email protected]. (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 December 22, 2016. Robert D. Breneman, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-31619 Filed 1-4-17; 8:45 am] BILLING CODE 4910-13-P
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installed, where ‘‘XX’’ is any two 1391–01 with IGB fairing P/N 332A24–0322– DEPARTMENT OF TRANSPORTATION
alphanumeric characters, certificated in any 00 in accordance with the Accomplishment
category. Instructions, paragraph 3.B.2, of SB No. Federal Aviation Administration
(b) Unsafe Condition AS332–53.01.78 or SB No. EC225–53–041.
(4) Replacing the IGB fairing with IGB 14 CFR Part 39
This AD defines the unsafe condition as
detachment of the angle section of an IGB fairing P/N 332A24–0322–00 is terminating
[Docket No. FAA–2016–9566; Directorate
and subsequent interference between an IGB action for the repetitive inspections required
Identifier 2016–NM–191–AD]
fairing and tail rotor inclined drive shaft. by this AD.
This condition could result in failure of a tail (5) Do not install an IGB fairing P/N RIN 2120–AA64
rotor drive shaft, loss of the tail rotor drive, 332A24–0303–05XX, P/N 332A24–0303–
and subsequent loss of control of the 06XX, P/N 332A08–1391–00, or P/N Airworthiness Directives; The Boeing
helicopter. 332A08–1391–01 on any helicopter. Company Airplanes
(c) Comments Due Date (f) Credit for Actions Previously Completed AGENCY: Federal Aviation
We must receive comments by March 6, Compliance with Airbus Helicopters Administration (FAA), DOT.
2017. ACTION: Notice of proposed rulemaking
Emergency Alert Service Bulletin No.
(d) Compliance 53.01.47, Revision 4, dated September 27, (NPRM).
You are responsible for performing each 2011, before the effective date of this AD is
considered acceptable for compliance with SUMMARY: We propose to adopt a new
action required by this AD within the
specified compliance time unless it has the initial inspections specified in airworthiness directive (AD) for all The
already been accomplished prior to that time. paragraphs (e)(1) and (e)(2) of this AD, but Boeing Company Model 757–200,
does not constitute terminating action for the –200PF, and –200CB series airplanes.
(e) Required Actions This proposed AD was prompted by an
repetitive inspections required by this AD.
(1) Within 15 hours time-in-service (TIS) evaluation by the design approval
and thereafter at intervals not to exceed 15 (g) Alternative Methods of Compliance holder (DAH) indicating that certain
hours TIS, visually inspect the IGB fairing (AMOCs) fuselage circumferential splice plates
and the left- and right-hand attachment
supports for a crack as shown in Figure 2 of (1) The Manager, Safety Management are subject to widespread fatigue
Airbus Helicopters Emergency Alert Service Group, FAA, may approve AMOCs for this damage (WFD). This proposed AD
Bulletin (EASB) No. 53.01.47, Revision 5, AD. Send your proposal to: David Hatfield, would require repetitive low frequency
dated March 5, 2015 (EASB No. 53.01.47) or Aviation Safety Engineer, Safety Management eddy current (LFEC) inspections for
EASB No. 53A001, Revision 5, dated March Group, Rotorcraft Directorate, FAA, 10101 cracks of certain circumferential splice
5, 2015 (EASB No. 53A001), as appropriate Hillwood Pkwy, Fort Worth, TX 76177; plates, and repairs if necessary. We are
for your model helicopter. telephone (817) 222–5116; email 9-ASW- proposing this AD to address the unsafe
(i) If there is a crack in an attachment FTW-AMOC-Requests@faa.gov. condition on these products.
support, replace the attachment support. (2) For operations conducted under a 14
(ii) If there is a crack in the fairing, replace DATES: We must receive comments on
CFR part 119 operating certificate or under this proposed AD by February 21, 2017.
the IGB fairing with IBG fairing P/N 332A24–
0322–00 in accordance with the 14 CFR part 91, subpart K, we suggest that
ADDRESSES: You may send comments,
Accomplishment Instructions, paragraph you notify your principal inspector, or
lacking a principal inspector, the manager of
using the procedures found in 14 CFR
3.B.2, of Airbus Helicopters Service Bulletin 11.43 and 11.45, by any of the following
No. AS332–53.01.78, Revision 0, dated the local flight standards district office or
March 9, 2015 (SB No. AS332–53.01.78) or certificate holding district office before methods:
Service Bulletin No. EC225–53–041, Revision operating any aircraft complying with this • Federal eRulemaking Portal: Go to
0, dated March 9, 2015 (SB No. EC225–53– AD through an AMOC. http://www.regulations.gov. Follow the
041), as appropriate for your model instructions for submitting comments.
helicopter. (h) Additional Information • Fax: 202–493–2251.
(2) For helicopters with IGB fairing P/N The subject of this AD is addressed in • Mail: U.S. Department of
332A24–0303–05XX or P/N 332A24–0303– European Aviation Safety Agency (EASA) AD Transportation, Docket Operations, M–
06XX, within 15 hours TIS and thereafter at 30, West Building Ground Floor, Room
No. 2015–0092, dated May 26, 2015. You
intervals not to exceed 15 hours TIS, visually
may view the EASA AD on the Internet at W12–140, 1200 New Jersey Avenue SE.,
inspect for a crack in the fairing gutter as
shown in Figure 1 of EASB No. 53.01.47 or http://www.regulations.gov in the AD Docket. Washington, DC 20590.
EASB No. 53A001. If there is a crack in the • Hand Delivery: Deliver to Mail
(i) Subject
fairing gutter: address above between 9 a.m. and 5
(i) Inspect for interference and separation Joint Aircraft Service Component (JASC) p.m., Monday through Friday, except
of the fairing gutter. If there is any Code: 5350 Aerodynamic Fairings. Federal holidays.
interference between the gutter and the tail For service information identified in
Issued in Fort Worth, Texas, on December
rotor inclined drive shaft tube, replace the this NPRM, contact Boeing Commercial
tail rotor inclined drive shaft tube. If there is 21, 2016.
Lance T. Gant, Airplanes, Attention: Contractual & Data
any interference between the gutter and a
hydraulic pipe, repair or replace the Services (C&DS), 2600 Westminster
Manager, Rotorcraft Directorate, Aircraft
hydraulic pipe. If there is any interference Blvd., MC 110–SK57, Seal Beach, CA
Certification Service.
between the gutter and the flight controls, 90740–5600; telephone 562–797–1717;
[FR Doc. 2016–31866 Filed 1–4–17; 8:45 am]
repair the flight controls in accordance with Internet https://
FAA-approved procedures. If there is any BILLING CODE 4910–13–P www.myboeingfleet.com. You may view
mstockstill on DSK3G9T082PROD with PROPOSALS
separation of the gutter, remove the gutter. this referenced service information at
(ii) Replace the IGB fairing with IBG fairing the FAA, Transport Airplane
P/N 332A24–0322–00 in accordance with the Directorate, 1601 Lind Avenue SW.,
Accomplishment Instructions, paragraph
3.B.2, of SB No. AS332–53.01.78 or SB No. Renton, WA. For information on the
EC225–53–041. availability of this material at the FAA,
(3) Within 150 hours TIS, replace the IGB call 425–227–1221. It is also available
fairing P/N 332A24–0303–05XX, 332A24– on the internet at http://
0303–06XX, 332A08–1391–00, or 332A08– www.regulations.gov by searching for
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ESTIMATED COSTS
Parts
Action Labor cost Cost per product Cost on U.S. operators
cost
LFEC inspection ................ 6 work-hours × $85 per hour = $0 $510 per inspection cycle ........... $323,340 per inspection cycle.
$510 per inspection cycle.
We have received no definitive data The Proposed Amendment paragraph (h)(1) of this AD: Do an LFEC
that would enable us to provide cost inspection for cracking of the circumferential
Accordingly, under the authority splice plates at station 900 and station 1180,
estimates for the on-condition actions delegated to me by the Administrator,
specified in this proposed AD. from stringer S–6L to stringer S–6R, and do
the FAA proposes to amend 14 CFR part all applicable corrective actions, in
Authority for This Rulemaking 39 as follows: accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
Title 49 of the United States Code PART 39—AIRWORTHINESS 757–53A0105, dated June 10, 2016, except as
specifies the FAA’s authority to issue DIRECTIVES required by paragraph (h)(2) of this AD. Do
rules on aviation safety. Subtitle I, all applicable corrective actions before
section 106, describes the authority of ■ 1. The authority citation for part 39 further flight. Repeat the inspections
the FAA Administrator. Subtitle VII: continues to read as follows: thereafter at the applicable times specified in
Aviation Programs, describes in more Authority: 49 U.S.C. 106(g), 40113, 44701. paragraph 1.E., ‘‘Compliance,’’ of Boeing
detail the scope of the Agency’s Alert Service Bulletin 757–53A0105, dated
authority. § 39.13 [Amended] June 10, 2016. Accomplishing these
We are issuing this rulemaking under ■ 2. The FAA amends § 39.13 by adding inspections terminates the requirements of
the authority described in Subtitle VII, the following new airworthiness paragraph (h) of AD 2006–11–11 for the
Part A, Subpart III, Section 44701: inspections of structurally significant item
directive (AD): (SSI) 53–40–05, circumferential skin splice
‘‘General requirements.’’ Under that
The Boeing Company: Docket No. FAA– body station BS900 stringer S–6L to stringer
section, Congress charges the FAA with 2016–9566; Directorate Identifier 2016– S–6R and circumferential skin splice body
promoting safe flight of civil aircraft in NM–191–AD. station BS1180 stringer S–6L to stringer S–
air commerce by prescribing regulations 6R, as specified in Section 9 of Boeing
for practices, methods, and procedures (a) Comments Due Date
Maintenance Planning Data (MPD) Document
the Administrator finds necessary for We must receive comments by February D622N001–9, May 2003 or June 2005
safety in air commerce. This regulation 21, 2017. revisions. All other provisions of AD 2006–
is within the scope of that authority (b) Affected ADs 11–11 remain fully applicable and must be
because it addresses an unsafe condition This AD affects AD 2006–11–11,
complied with.
that is likely to exist or develop on Amendment 39–14615 (71 FR 30278, May 26, (h) Service Information Exceptions
products identified in this rulemaking 2006) (‘‘AD 2006–11–11’’). (1) Where Boeing Alert Service Bulletin
action.
(c) Applicability 757–53A0105, dated June 10, 2016, specifies
Regulatory Findings a compliance time ‘‘after the original issue
This AD applies to all The Boeing
date of this service bulletin,’’ this AD
We determined that this proposed AD Company Model 757–200, –200PF, and
requires compliance within the specified
would not have federalism implications –200CB series airplanes, certificated in any
compliance time after the effective date of
under Executive Order 13132. This category.
this AD.
proposed AD would not have a (d) Subject (2) Where Boeing Alert Service Bulletin
substantial direct effect on the States, on Air Transport Association (ATA) of 757–53A0105, dated June 10, 2016, specifies
the relationship between the national America Code 53, Fuselage. to contact Boeing for repair instructions, and
Government and the States, or on the specifies that action as Required for
distribution of power and (e) Unsafe Condition Compliance (RC), this AD requires repair
responsibilities among the various This AD was prompted by an evaluation by using a method approved in accordance with
the design approval holder (DAH) indicating the procedures specified in paragraph (i) of
levels of government.
that the fuselage circumferential splice plates this AD.
For the reasons discussed above, I
along the center fastener rows, forward and
certify this proposed regulation: (i) Alternative Methods of Compliance
aft of station 900 and station 1180 splice
(1) Is not a ‘‘significant regulatory (AMOCs)
centerlines, are subject to widespread fatigue
action’’ under Executive Order 12866, damage (WFD). We are issuing this AD to (1) The Manager, Los Angeles Aircraft
(2) Is not a ‘‘significant rule’’ under detect and correct any such cracks, which Certification Office (ACO), FAA, has the
the DOT Regulatory Policies and could lead to the failure of a principal authority to approve AMOCs for this AD, if
Procedures (44 FR 11034, February 26, structural element and consequently requested using the procedures found in 14
1979), adversely affect the structural integrity of the CFR 39.19. In accordance with 14 CFR 39.19,
(3) Will not affect intrastate aviation airplane. send your request to your principal inspector
in Alaska, and or local Flight Standards District Office, as
(f) Compliance appropriate. If sending information directly
(4) Will not have a significant
Comply with this AD within the to the manager of the ACO, send it to the
mstockstill on DSK3G9T082PROD with PROPOSALS
economic impact, positive or negative,
compliance times specified, unless already attention of the person identified in
on a substantial number of small entities
done. paragraph (j)(1) of this AD. Information may
under the criteria of the Regulatory be emailed to: 9-ANM-LAACO-AMOC-
Flexibility Act. (g) Repetitive Low Frequency Eddy Current Requests@faa.gov.
(LFEC) Inspections and Corrective Actions (2) Before using any approved AMOC,
List of Subjects in 14 CFR Part 39
At the applicable time specified in notify your appropriate principal inspector,
Air transportation, Aircraft, Aviation paragraph 1.E., ‘‘Compliance,’’ of Boeing or lacking a principal inspector, the manager
safety, Incorporation by reference, Alert Service Bulletin 757–53A0105, dated of the local flight standards district office/
Safety. June 10, 2016, except as required by certificate holding district office.
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(3) An AMOC that provides an acceptable DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m.
level of safety may be used for any repair, and 5 p.m., Monday through Friday,
modification, or alteration required by this Federal Aviation Administration except Federal holidays. The AD docket
AD if it is approved by the Boeing contains this proposed AD, the
Commercial Airplanes Organization 14 CFR Part 39 regulatory evaluation, any comments
Designation Authorization (ODA) that has received, and other information. The
[Docket No. FAA–2016–9405; Directorate
been authorized by the Manager, Los Angeles street address for the Docket Office
Identifier 2016–NE–22–AD]
ACO, to make those findings. To be (phone: 800–647–5527) is in the
approved, the repair method, modification RIN 2120–AA64 ADDRESSES section. Comments will be
deviation, or alteration deviation must meet available in the AD docket shortly after
the certification basis of the airplane, and the Airworthiness Directives; Pratt & receipt.
approval must specifically refer to this AD. Whitney Division Turbofan Engines
FOR FURTHER INFORMATION CONTACT:
(4) Except as required by paragraph (h) of Kevin Clark, Aerospace Engineer,
AGENCY: Federal Aviation
this AD: For service information that Engine Certification Office, FAA, Engine
Administration (FAA), DOT.
contains steps that are labeled as RC, the & Propeller Directorate, 1200 District
provisions of paragraphs (i)(4)(i) and (i)(4)(ii) ACTION: Notice of proposed rulemaking
(NPRM). Avenue, Burlington, MA 01803; phone:
of this AD apply. 781–238–7088; fax: 781–238–7199;
(i) The steps labeled as RC, including
We propose to adopt a new
SUMMARY: email: kevin.m.clark@faa.gov.
substeps under an RC step and any figures
airworthiness directive (AD) for certain SUPPLEMENTARY INFORMATION:
identified in an RC step, must be done to
Pratt & Whitney Division (PW) PW2037,
comply with the AD. If a step or substep is
PW2037M, and PW2040 turbofan Comments Invited
labeled ‘‘RC Exempt,’’ then the RC
engines. This proposed AD was We invite you to send any written
requirement is removed from that step or
prompted by an unrecoverable engine relevant data, views, or arguments about
substep. An AMOC is required for any
in-flight shutdown (IFSD) after an ice this NPRM. Send your comments to an
deviations to RC steps, including substeps
crystal icing event. This proposed AD address listed under the section. Include
and identified figures.
would require installing a software ‘‘Docket No. FAA–2016–9405;
(ii) Steps not labeled as RC may be
standard eligible for installation and Directorate Identifier 2016–NE–22–AD’’
deviated from using accepted methods in
preclude the use of electronic engine at the beginning of your comments. We
accordance with the operator’s maintenance
control (EEC) software standards earlier specifically invite comments on the
or inspection program without obtaining
than SCN 5B/I. We are proposing this overall regulatory, economic,
approval of an AMOC, provided the RC steps,
AD to correct the unsafe condition on environmental, and energy aspects of
including substeps and identified figures, can
these products. this NPRM. We will consider all
still be done as specified, and the airplane
DATES: We must receive comments on
comments received by the closing date
can be put back in an airworthy condition.
this proposed AD by February 21, 2017. and may amend this NPRM because of
(j) Related Information those comments.
ADDRESSES: You may send comments, We will post all comments we
(1) For more information about this AD, using the procedures found in 14 CFR
contact Eric Schrieber, Aerospace Engineer, receive, without change, to http://
11.43 and 11.45, by any of the following www.regulations.gov, including any
Airframe Branch, ANM–120L, FAA, Los methods:
Angeles ACO, 3960 Paramount Boulevard, personal information you provide. We
• Federal eRulemaking Portal: Go to will also post a report summarizing each
Lakewood, CA 90712–4137; phone: 562–627–
http://www.regulations.gov. Follow the substantive verbal contact we receive
5348; fax: 562–627–5210; email:
instructions for submitting comments. about this NPRM.
eric.schrieber@faa.gov.
• Fax: 202–493–2251.
(2) For service information identified in
• Mail: U.S. Department of Discussion
this AD, contact Boeing Commercial
Transportation, Docket Operations, We propose to adopt an AD for certain
Airplanes, Attention: Contractual & Data
M–30, West Building Ground Floor, PW PW2037, PW2037M, and PW2040
Services (C&DS), 2600 Westminster Blvd.,
Room W12–140, 1200 New Jersey turbofan engines with EEC, model
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
Avenue SE., Washington, DC 20590. number EEC104–40 or EEC104–60,
www.myboeingfleet.com. You may view this
• Hand Delivery: Deliver to Mail installed with an EEC software standard
referenced service information at the FAA,
address above between 9 a.m. and 5 earlier than SCN 5B/I. This proposed
Transport Airplane Directorate, 1601 Lind p.m., Monday through Friday, except AD was prompted by a report of an
Avenue SW., Renton, WA. For information Federal holidays. unrecoverable engine IFSD after an ice
on the availability of this material at the For service information identified in crystal icing event. The root cause of the
FAA, call 425–227–1221. this NPRM, contact Pratt & Whitney event is ice crystal icing causing the
Division, 400 Main St., East Hartford, engine to flameout. An attempt to restart
Issued in Renton, Washington, on CT 06118; phone: 800–565–0140; fax: the engine was made while the active
December 22, 2016. 860–565–5442. You may view this clearance control was on, which caused
Robert D. Breneman, service information at the FAA, Engine damage to the HPT and rotor seizure.
Acting Manager, Transport Airplane & Propeller Directorate, 1200 District This condition, if not corrected, could
Directorate, Aircraft Certification Service. Avenue, Burlington, MA. For result in failure of the HPT, rotor
information on the availability of this seizure, failure of one or more engines,
mstockstill on DSK3G9T082PROD with PROPOSALS
[FR Doc. 2016–31619 Filed 1–4–17; 8:45 am]
BILLING CODE 4910–13–P material at the FAA, call 781–238–7125. loss of thrust control, and loss of the
Examining the AD Docket airplane.
You may examine the AD docket on Related Service Information Under
the Internet at http:// 1 CFR Part 51
www.regulations.gov by searching for We reviewed PW Alert Service
and locating Docket No. FAA–2016– Bulletin (ASB) PW2000 A73–170, dated
9405; or in person at the Docket July 14, 2016. The ASB describes
VerDate Sep<11>2014 20:07 Jan 04, 2017 Jkt 241001 PO 00000 Frm 00035 Fmt 4702 Sfmt 4702 E:\FR\FM\05JAP1.SGM 05JAP1](https://thefederalregister.org/doc/82_FR_1265/page/4.svg)
Document Created: 2018-02-01 14:51:12
Document Modified: 2018-02-01 14:51:12
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by February 21, 2017. | |
| Contact | Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 82 FR 1262 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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