82 FR 13567 - Airworthiness Directives; Various Model 234 and Model CH-47D Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 48 (March 14, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 48 (March 14, 2017)
| Page Range | 13567-13569 | |
| FR Document | 2017-04735 |
[Federal Register Volume 82, Number 48 (Tuesday, March 14, 2017)] [Proposed Rules] [Pages 13567-13569] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-04735] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4007; Directorate Identifier 2015-SW-064-AD] RIN 2120-AA64 Airworthiness Directives; Various Model 234 and Model CH-47D Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for various Model 234 and Model CH-47D helicopters. This proposed AD would require inspections of the pitch housing and revising the pitch housing retirement life. This proposed AD is prompted by reports of cracking in the pitch housing lugs. The proposed actions are intended to detect and prevent an unsafe condition on these products. DATES: We must receive comments on this proposed AD by May 15, 2017. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. Fax: 202-493-2251. Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001. Hand Delivery: Deliver to the ``Mail'' address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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-2015- 4007; 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 economic evaluation, the Special Airworthiness Information Bulletin (SAIB), 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 service information identified in this proposed AD, contact Boeing Helicopters, The Boeing Company, 1 S. Stewart Avenue, Ridley Park, PA 19078, telephone 610-591-2121, and Columbia Helicopters, Inc. (Columbia), 14452 Arndt Road NE., Aurora OR 97002, telephone (503) 678- 1222, fax (503) 678-5841, or at http://www.colheli.com. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Kathleen Arrigotti, Aerospace Engineer, Seattle Aircraft Certification Office, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057; telephone (425) 917-6426; email [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring [[Page 13568]] expense or delay. We may change this proposal in light of the comments we receive. Discussion We propose to adopt an AD for helicopters with a pitch housing part number (P/N) 145R2075-11, 145R2075-12, 145R2075-13, 145R2075-14, 145R2075-15, 145R2075-16, 234R2075-1, or 234R2075-2 installed. These pitch housings are installed on Model 234 and Model CH-47D helicopters. The type certificate (TC) holder for Model 234 helicopters is Columbia (type certificate previously held by Boeing Defense & Space Group), and the type certificate holders for Model CH-47D helicopters currently include Columbia, Billings Flying Service, Inc., and Tandem Rotor, LLC. We are not limiting this proposed AD to the type certificate holders listed above because we expect additional type certificate holders of helicopters that are subject to this same unsafe condition. This proposed AD is prompted by reports of cracking in the pitch housing lugs. In November 2007, Boeing reported the failure of an aft rotor pitch housing lower lug on a Model CH-47 helicopter operated by the Japanese Ground Self Defense Force. On March 26, 2009, a Model 234 helicopter also experienced a failure because of a crack on an aft rotor pitch housing lower lug. In both cases, the cracking was located on the lead side of the lower vertical pin lug and had initiated in the bore. The crack grew outward by fatigue, initiated by fretting damage. Those incidents prompted the FAA to issue SAIB SW-11-03, dated October 22, 2010. The SAIB recommends that all owners and operators of Columbia Model 234 helicopters perform repetitive ultrasonic inspections of the lugs. At that time, there were no civil Model CH-47D helicopters in service. On March 20, 2015, we received a report of lateral vibration on a Model 234 helicopter that prompted an immediate landing. A subsequent investigation found that a crack in an aft pitch housing upper lug resulted in the lateral vibrations. The pitch housing had accumulated 11,733 hours time-in-service (TIS). The crack was determined to be caused by fatigue and attributed to underestimated load conditions in the original life limit calculations. This cracking differed from the cracking described in the SAIB because the cracking initiated at the outer surface of the pitch housing lug and grew inward toward the bore. To correct this unsafe condition, we propose to require repetitive eddy current and ultrasonic inspections of the pitch housing. Based on the proximity of the most recent inward-growing crack to the outward cracks described in the SAIB, we propose to require ultrasonic inspections of the pitch housing, as recommended in the SAIB. Boeing, the original manufacturer of both model helicopters, developed service information for the SAIB ultrasonic inspections, which we would require in this proposed AD. Due to the rapid growth rate, an effective eddy current inspection must detect an inward-growing crack of no more than 0.10 inch. This proposed AD would require, for Columbia helicopters, the eddy current inspection method specified in Columbia's service information. Because the other TC holders have not developed service instructions, we propose to require the eddy current inspection procedures for all other helicopters be submitted to the Seattle or Denver Aircraft Certification Offices for approval. We are also proposing to require removing the pitch housing from service when it accumulates a total of 8,200 hours TIS. Forward pitch housings on Model CH-47D helicopters have no life limit and the aft pitch housing already has a life limit of 8,200 hours TIS. For Model 234 helicopters, the forward pitch housing has a life limit of 12,547 hours TIS and the aft pitch housing has a life limit of 19,077 hours TIS. This proposed AD would establish or reduce these life limits to 8,200 hours TIS for both forward and aft pitch housings, regardless of the model helicopter. The actions specified by this proposed AD are intended to detect and prevent a crack in a pitch housing lug. This condition could result in loss of a rotor blade and consequent loss of helicopter control. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin 145R2075-62-0001, Revision 1, dated September 27, 2011, which specifies updated life limits for the forward and aft pitch housings and revised overhaul and ultrasonic inspection procedures for various military Model CH-47 and 234 helicopters. We also reviewed Columbia Helicopters, Inc., Alert Service Bulletin No. 234-62-A0012, Revision 2, dated March 1, 2016, for Model 234 helicopters; and Alert Service Bulletin No. 47D-62-A0002, Revision 0, dated March 1, 2016, for Model CH-47D helicopters. This service information specifies procedures for performing repetitive eddy current inspections, visual inspections, and ultrasonic inspections and for reducing the life limit of the pitch housing assemblies. 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. Proposed AD Requirements This proposed AD would require: Before further flight, removing from service any pitch housing P/N 145R2075-11, 145R2075-12, 145R2075-13, 145R2075-14, 145R2075-15, 145R2075-16, 234R2075-1, and 234R2075-2 that has accumulated 8,200 hours total time-in-service (TIS). Before the pitch housing accumulates 200 hours TIS after the effective date of this proposed AD and thereafter at intervals not to exceed 200 hours TIS, ultrasonic inspecting the pitch housing for a crack and replacing any cracked pitch housing. Within 400 hours TIS or before the pitch housing accumulates 4,000 hours total TIS, whichever occurs later, and thereafter at intervals not to exceed 500 hours TIS, eddy current inspecting the pitch housing for a crack and replacing any cracked pitch housing. For Columbia helicopters, this eddy current inspection would be performed in accordance with the Columbia service information. For all other helicopters, this proposed AD would require that the method for the eddy current inspection be approved by the Manager, Seattle Aircraft Certification Office (ACO) or Manager, Denver ACO. Differences Between This Proposed AD and the Service Information The service information provides different life limits for the forward and aft pitch housings, while this proposed AD would require a life limit of 8,200 hours TIS for all pitch housings. The service information requires either an ultrasonic inspection or a dye penetrant inspection as part of the overhaul procedures. The service information specifies different compliance times for the inspections than what would be required by this proposed AD. Costs of Compliance We estimate that this proposed AD would affect 15 helicopters of U.S. Registry and that labor costs would average $85 per work-hour. Based on [[Page 13569]] these estimates, we expect the following costs: An eddy current inspection would require 4 work-hours for a total cost of $340 per helicopter and $5,100 for the U.S. fleet, per inspection cycle. An ultrasonic inspection would require 4 work-hours for a total cost of $340 per helicopter and $5,100 for the U.S. fleet, per inspection cycle. Replacing a pitch housing would require 8 work-hours and parts would cost $13,000, for a total cost of $13,680 per helicopter. 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, I certify that this proposed AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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 an economic 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 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): Various Model 234 and Model CH-47D Helicopters: Docket No. FAA-2015- 4007; Directorate Identifier 2015-SW-64-AD. (a) Applicability This AD applies to Model 234 and Model CH-47D helicopters, regardless of type certificate holder, with a pitch housing assembly (pitch housing) part number (P/N) 145R2075-11, 145R2075-12, 145R2075-13, 145R2075-14, 145R2075-15, 145R2075-16, 234R2075-1, or 234R2075-2 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a pitch housing lug. This condition could result in loss of a rotor blade and consequent loss of helicopter control. (c) Comments Due Date We must receive comments by May 15, 2017. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Before further flight, remove from service any pitch housing P/N 145R2075-11, 145R2075-12, 145R2075-13, 145R2075-14, 145R2075-15, 145R2075-16, 234R2075-1, and 234R2075-2 that has accumulated 8,200 hours total time-in-service (TIS). (2) Before the pitch housing accumulates 200 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 200 hours TIS, ultrasonic inspect the pitch housing for a crack in accordance with Attachment 1, paragraphs F and H through K, of Boeing Service Bulletin 145R2075-62-0001, Revision 1, dated September 27, 2011. If there is a crack, replace the pitch housing before further flight. (3) Within 400 hours TIS or before the pitch housing has accumulated 4,000 hours total TIS, whichever occurs later, and thereafter at intervals not to exceed 500 hours TIS: (i) For Columbia Helicopters, Inc., Model 234 and CH-47D helicopters, eddy current inspect the pitch housing for a crack by following paragraphs 3.C.(1) and 3.C.(2) of Columbia Helicopters, Inc., Alert Service Bulletin No. 234-62-A0012, Revision 2, dated March 1, 2016, or Alert Service Bulletin No. 47D-62-A0002, Revision 0, dated March 1, 2016, as applicable to your model helicopter. If there is a crack, replace the pitch housing before further flight. (ii) For all other helicopters, eddy current inspect the pitch housing for a crack. If there is a crack, replace the pitch housing before further flight. The eddy current inspection must be accomplished using a method approved by the Manager, Seattle Aircraft Certification Office (ACO) or Manager, Denver ACO. For a repair method to be approved as required by this AD, the Manager's approval letter must specifically refer to this AD. (f) Alternative Methods of Compliance (AMOCs) (1) For operators of helicopters with type certificates issued by the Denver Aircraft Certification Office, the manager of the Denver Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Greg Johnson, Senior Aerospace Engineer, Denver Aircraft Certification Office, 26805 East 68th Avenue, Denver, CO 80249; phone: 303-342-1083; fax: 303-342-1088; email: [email protected]. (2) All other AMOC requests should be sent to the Manager, Seattle Aircraft Certification Office, FAA. Send your proposal to: Kathleen Arrigotti, Aerospace Engineer, Seattle Aircraft Certification Office, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057; telephone (425) 917-6426; email [email protected]. (3) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (g) Additional Information Special Airworthiness Information Bulletin SW-11-03, dated October 22, 2010 (SAIB), which is not incorporated by reference, contains additional information about the subject of this AD. You may view the SAIB on the internet at http://www.regulations.gov in the AD Docket. (h) Subject Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor Head. Issued in Fort Worth, Texas, on March 1, 2017. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2017-04735 Filed 3-13-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 48 / Tuesday, March 14, 2017 / Proposed Rules 13567
0–00 with P/N MC7015–1–00. P/N MC7014– www.regulations.gov in Docket No. FAA– www.regulations.gov by searching for
1–00 and P/N MC7015–1–00 must be from 2016–9143. and locating Docket No. FAA–2015–
the same manufacturer. 4007; or in person at the Docket
(i) Subject
(iii) Modify and re-identify the helicopter Operations Office between 9 a.m. and 5
wiring harness. Refer to Figure 3 of Joint Aircraft Service Component (JASC)
Eurocopter Alert Service Bulletin No. EC225– Code: 6320, Main Rotor Gearbox. p.m., Monday through Friday, except
05A033, Revision 0, dated July 14, 2013 (ASB Federal holidays. The AD docket
Issued in Fort Worth, Texas, on March 1,
EC225–05A033). contains this proposed AD, the
2017.
(iv) Replace MGB lubrication card P/N economic evaluation, the Special
Scott A. Horn,
704A46580127 with P/N 704A46580146, and Airworthiness Information Bulletin
MGB lubrication card P/N 704A46580106 Acting Manager, Rotorcraft Directorate, (SAIB), any comments received, and
with P/N 704A46580146 or –147. Aircraft Certification Service.
other information. The street address for
(v) Accomplish a functional test of the [FR Doc. 2017–04736 Filed 3–13–17; 8:45 am] the Docket Operations Office (telephone
EMLUB system and the electrical system. BILLING CODE 4910–13–P 800–647–5527) is in the ADDRESSES
(vi) Revise the Emergency Procedures
section. Comments will be available in
section of the Rotorcraft Flight Manual (RFM)
by removing any pages from Section 3 of the the AD docket shortly after receipt.
DEPARTMENT OF TRANSPORTATION For service information identified in
RFM that pertain to the emergency
procedures in the event of EMLUB activation this proposed AD, contact Boeing
Federal Aviation Administration
and by inserting the pages from paragraph Helicopters, The Boeing Company, 1 S.
4.C. Appendix 3, of ASB EC225–05A033 into Stewart Avenue, Ridley Park, PA 19078,
14 CFR Part 39
Section 3 of the RFM. telephone 610–591–2121, and Columbia
(2) Do not install on any helicopter EMLUB [Docket No. FAA–2015–4007; Directorate Helicopters, Inc. (Columbia), 14452
glycol pump P/N 332A32–5051–00, air Identifier 2015–SW–064–AD] Arndt Road NE., Aurora OR 97002,
pressure-switch P/N MA193–00 or P/N telephone (503) 678–1222, fax (503)
MC7014–0–00, glycol pressure-switch P/N RIN 2120–AA64
678–5841, or at http://www.colheli.com.
MA194–01 or P/N MC7015–0–00, or
electronic board P/N 704A46580106 or P/N Airworthiness Directives; Various You may review the referenced service
704A46580127. Model 234 and Model CH–47D information at the FAA, Office of the
Helicopters Regional Counsel, Southwest Region,
(f) Special Flight Permit 10101 Hillwood Pkwy., Room 6N–321,
Special flight permits are prohibited. AGENCY: Federal Aviation Fort Worth, TX 76177.
(g) Alternative Methods of Compliance
Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT:
(AMOCs) ACTION: Notice of proposed rulemaking Kathleen Arrigotti, Aerospace Engineer,
(1) The Manager, Safety Management (NPRM). Seattle Aircraft Certification Office,
Group, FAA, may approve AMOCs for this Transport Airplane Directorate, FAA,
AD. Send your proposal to Rao Edupuganti, SUMMARY: We propose to adopt a new 1601 Lind Avenue SW., Renton,
Aviation Safety Engineer, Regulations and airworthiness directive (AD) for various Washington 98057; telephone (425)
Policy Group, Rotorcraft Directorate, FAA, Model 234 and Model CH–47D 917–6426; email Kathleen.Arrigotti@
10101 Hillwood Pkwy., Fort Worth, Texas helicopters. This proposed AD would faa.gov.
76177; telephone (817) 222–5110; email require inspections of the pitch housing
rao.edupuganti@faa.gov. and revising the pitch housing SUPPLEMENTARY INFORMATION:
(2) For operations conducted under a 14 retirement life. This proposed AD is Comments Invited
CFR part 119 operating certificate or under prompted by reports of cracking in the
14 CFR part 91, subpart K, we suggest that
pitch housing lugs. The proposed We invite you to participate in this
you notify your principal inspector, or
actions are intended to detect and rulemaking by submitting written
lacking a principal inspector, the manager of comments, data, or views. We also
the local flight standards district office or prevent an unsafe condition on these
products. invite comments relating to the
certificate holding district office before economic, environmental, energy, or
operating any aircraft complying with this DATES: We must receive comments on
AD through an AMOC.
federalism impacts that might result
this proposed AD by May 15, 2017. from adopting the proposals in this
(h) Additional Information ADDRESSES: You may send comments by document. The most helpful comments
(1) Emergency Alert Service Bulletin (ASB) any of the following methods: reference a specific portion of the
No.05A032, Revision 2, dated July 14, 2013, • Federal eRulemaking Docket: Go to proposal, explain the reason for any
and Emergency ASB with two numbers (No. http://www.regulations.gov. Follow the recommended change, and include
04A010 and No. 04A009), Revision 1, dated online instructions for sending your supporting data. To ensure the docket
July 14, 2013, which are not incorporated by does not contain duplicate comments,
comments electronically.
reference, contain additional information
about the subject of this AD. For service • Fax: 202–493–2251. commenters should send only one copy
information identified in this AD, contact • Mail: Send comments to the U.S. of written comments, or if comments are
Airbus Helicopters, 2701 N. Forum Drive, Department of Transportation, Docket filed electronically, commenters should
Grand Prairie, TX 75052; telephone (972) Operations, M–30, West Building submit only one time.
641–0000 or (800) 232–0323; fax (972) 641– Ground Floor, Room W12–140, 1200 We will file in the docket all
3775; or at http:// New Jersey Avenue SE., Washington, comments that we receive, as well as a
www.airbushelicopters.com/techpub. You DC 20590–0001. report summarizing each substantive
rmajette on DSK30RV082PROD with PROPOSALS
may review the referenced service • Hand Delivery: Deliver to the public contact with FAA personnel
information at the FAA, Office of the concerning this proposed rulemaking.
‘‘Mail’’ address between 9 a.m. and 5
Regional Counsel, Southwest Region, 10101
p.m., Monday through Friday, except Before acting on this proposal, we will
Hillwood Pkwy., Room 6N–321, Fort Worth,
Texas 76177. Federal holidays. consider all comments we receive on or
(2) The subject of this AD is addressed in before the closing date for comments.
Examining the AD Docket We will consider comments filed after
European Aviation Safety Agency (EASA) AD
2013–0156, dated July 18, 2013. You may You may examine the AD docket on the comment period has closed if it is
view the EASA AD on the Internet at http:// the Internet at http:// possible to do so without incurring
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these estimates, we expect the following this proposed AD and placed it in the total TIS, whichever occurs later, and
costs: AD docket. thereafter at intervals not to exceed 500 hours
• An eddy current inspection would TIS:
List of Subjects in 14 CFR Part 39 (i) For Columbia Helicopters, Inc., Model
require 4 work-hours for a total cost of 234 and CH–47D helicopters, eddy current
$340 per helicopter and $5,100 for the Air transportation, Aircraft, Aviation
inspect the pitch housing for a crack by
U.S. fleet, per inspection cycle. safety, Incorporation by Reference, following paragraphs 3.C.(1) and 3.C.(2) of
• An ultrasonic inspection would Safety. Columbia Helicopters, Inc., Alert Service
require 4 work-hours for a total cost of The Proposed Amendment Bulletin No. 234–62–A0012, Revision 2,
$340 per helicopter and $5,100 for the dated March 1, 2016, or Alert Service
Accordingly, under the authority Bulletin No. 47D–62–A0002, Revision 0,
U.S. fleet, per inspection cycle.
delegated to me by the Administrator, dated March 1, 2016, as applicable to your
• Replacing a pitch housing would model helicopter. If there is a crack, replace
the FAA proposes to amend 14 CFR part
require 8 work-hours and parts would the pitch housing before further flight.
39 as follows:
cost $13,000, for a total cost of $13,680 (ii) For all other helicopters, eddy current
per helicopter. PART 39—AIRWORTHINESS inspect the pitch housing for a crack. If there
DIRECTIVES is a crack, replace the pitch housing before
Authority for This Rulemaking further flight. The eddy current inspection
Title 49 of the United States Code ■ 1. The authority citation for part 39 must be accomplished using a method
approved by the Manager, Seattle Aircraft
specifies the FAA’s authority to issue continues to read as follows: Certification Office (ACO) or Manager,
rules on aviation safety. Subtitle I, Authority: 49 U.S.C. 106(g), 40113, 44701. Denver ACO. For a repair method to be
section 106, describes the authority of approved as required by this AD, the
the FAA Administrator. ‘‘Subtitle VII: § 39.13 [Amended] Manager’s approval letter must specifically
Aviation Programs,’’ describes in more ■ 2. The FAA amends § 39.13 by adding refer to this AD.
detail the scope of the Agency’s the following new airworthiness (f) Alternative Methods of Compliance
authority. directive (AD): (AMOCs)
We are issuing this rulemaking under Various Model 234 and Model CH–47D (1) For operators of helicopters with type
the authority described in ‘‘Subtitle VII, Helicopters: Docket No. FAA–2015– certificates issued by the Denver Aircraft
Part A, Subpart III, Section 44701: 4007; Directorate Identifier 2015–SW– Certification Office, the manager of the
General requirements.’’ Under that 64–AD. Denver Aircraft Certification Office, FAA,
section, Congress charges the FAA with (a) Applicability may approve AMOCs for this AD. Send your
promoting safe flight of civil aircraft in proposal to: Greg Johnson, Senior Aerospace
This AD applies to Model 234 and Model Engineer, Denver Aircraft Certification
air commerce by prescribing regulations CH–47D helicopters, regardless of type Office, 26805 East 68th Avenue, Denver, CO
for practices, methods, and procedures certificate holder, with a pitch housing 80249; phone: 303–342–1083; fax: 303–342–
the Administrator finds necessary for assembly (pitch housing) part number (P/N) 1088; email: Gregory.Johnson@faa.gov.
safety in air commerce. This regulation 145R2075–11, 145R2075–12, 145R2075–13, (2) All other AMOC requests should be
is within the scope of that authority 145R2075–14, 145R2075–15, 145R2075–16, sent to the Manager, Seattle Aircraft
because it addresses an unsafe condition 234R2075–1, or 234R2075–2 installed, Certification Office, FAA. Send your
that is likely to exist or develop on certificated in any category. proposal to: Kathleen Arrigotti, Aerospace
products identified in this rulemaking (b) Unsafe Condition Engineer, Seattle Aircraft Certification Office,
Transport Airplane Directorate, FAA, 1601
action. This AD defines the unsafe condition as a Lind Avenue SW., Renton, Washington
crack in a pitch housing lug. This condition 98057; telephone (425) 917–6426; email 9-
Regulatory Findings could result in loss of a rotor blade and ANM-Seattle-ACO–AMOC-Requests@faa.gov.
We determined that this proposed AD consequent loss of helicopter control. (3) For operations conducted under a 14
would not have federalism implications (c) Comments Due Date CFR part 119 operating certificate or under
under Executive Order 13132. This We must receive comments by May 15,
14 CFR part 91, subpart K, we suggest that
proposed AD would not have a you notify your principal inspector, or
2017.
substantial direct effect on the States, on lacking a principal inspector, the manager of
the relationship between the national (d) Compliance the local flight standards district office or
You are responsible for performing each certificate holding district office before
Government and the States, or on the operating any aircraft complying with this
distribution of power and action required by this AD within the
specified compliance time unless it has AD through an AMOC.
responsibilities among the various
already been accomplished prior to that time. (g) Additional Information
levels of government. For the reasons
discussed, I certify that this proposed (e) Required Actions Special Airworthiness Information Bulletin
AD: (1) Before further flight, remove from SW–11–03, dated October 22, 2010 (SAIB),
1. Is not a ‘‘significant regulatory service any pitch housing P/N 145R2075–11, which is not incorporated by reference,
145R2075–12, 145R2075–13, 145R2075–14, contains additional information about the
action’’ under Executive Order 12866; subject of this AD. You may view the SAIB
2. Is not a ‘‘significant rule’’ under 145R2075–15, 145R2075–16, 234R2075–1,
and 234R2075–2 that has accumulated 8,200 on the internet at http://www.regulations.gov
DOT Regulatory Policies and Procedures hours total time-in-service (TIS). in the AD Docket.
(44 FR 11034, February 26, 1979); (2) Before the pitch housing accumulates (h) Subject
3. Will not affect intrastate aviation in 200 hours TIS after the effective date of this
Alaska to the extent that it justifies AD and thereafter at intervals not to exceed Joint Aircraft Service Component (JASC)
Code: 6220, Main Rotor Head.
rmajette on DSK30RV082PROD with PROPOSALS
making a regulatory distinction; and 200 hours TIS, ultrasonic inspect the pitch
4. Will not have a significant housing for a crack in accordance with Issued in Fort Worth, Texas, on March 1,
economic impact, positive or negative, Attachment 1, paragraphs F and H through K, 2017.
of Boeing Service Bulletin 145R2075–62– Scott A. Horn,
on a substantial number of small entities
0001, Revision 1, dated September 27, 2011.
under the criteria of the Regulatory If there is a crack, replace the pitch housing
Acting Manager, Rotorcraft Directorate,
Flexibility Act. Aircraft Certification Service.
before further flight.
We prepared an economic evaluation (3) Within 400 hours TIS or before the [FR Doc. 2017–04735 Filed 3–13–17; 8:45 am]
of the estimated costs to comply with pitch housing has accumulated 4,000 hours BILLING CODE 4910–13–P
VerDate Sep<11>2014 15:12 Mar 13, 2017 Jkt 241001 PO 00000 Frm 00005 Fmt 4702 Sfmt 9990 E:\FR\FM\14MRP1.SGM 14MRP1](https://thefederalregister.org/doc/82_FR_13615/page/3.svg)
Document Created: 2017-03-14 02:51:54
Document Modified: 2017-03-14 02:51:54
| 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 May 15, 2017. | |
| Contact | Kathleen Arrigotti, Aerospace Engineer, Seattle Aircraft Certification Office, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057; telephone (425) 917-6426; email [email protected] | |
| FR Citation | 82 FR 13567 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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