80 FR 32445 - Airworthiness Directives; Agusta S.p.A. (Agusta) Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 110 (June 9, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 110 (June 9, 2015)
| Page Range | 32445-32449 | |
| FR Document | 2015-13845 |
[Federal Register Volume 80, Number 110 (Tuesday, June 9, 2015)] [Rules and Regulations] [Pages 32445-32449] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-13845] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1937; Directorate Identifier 2014-SW-067-AD; Amendment 39-18171; AD 2015-11-08] RIN 2120-AA64 Airworthiness Directives; Agusta S.p.A. (Agusta) Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are superseding airworthiness directive (AD) 2014-02-08 for Agusta Model A109C, A109S, A109K2, A109E, and AW109SP helicopters. AD 2014-02-08 required inspecting the lock wires securing the tail rotor (T/R) duplex bearing locking nut (locking nut) to determine whether any lock wires are missing or damaged. This AD retains some of the requirements of AD 2014-02-08 but removes the terminating action, expands the applicability, and adds a daily pilot check. This AD was prompted by reports of loosening T/R locking nuts. These actions are intended to prevent failure of the T/R and subsequent loss of control of the helicopter. DATES: This AD becomes effective June 24, 2015. We must receive comments on this AD by August 10, 2015. 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 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 AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments [[Page 32446]] 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 AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331- 664757; fax 39-0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Martin Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email martin.r.crane@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, 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 resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, 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 them 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 rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion On January 16, 2014, we issued AD 2014-02-08, Amendment 39-17736 (79 FR 5257, January 31, 2014) for Agusta Model A109C, A109S, and A109K2 helicopters, and certain serial-numbered Model A109E and AW109SP helicopters. AD 2014-02-08 required repetitively inspecting the lock wires securing the T/R locking nut to determine whether any lock wires are missing or damaged, installing a second lock wire if only one was installed, and reassembling the housing and slider group of the T/R rotating controls as terminating action for the inspections. AD 2014- 02-08 was prompted by reports of loosening T/R locking nuts. Those actions are intended to prevent failure of the T/R and subsequent loss of control of the helicopter. AD 2014-02-08 was prompted by AD No. 2012-0195-E, dated September 24, 2012, and corrected September 25, 2012, issued by EASA, the Technical Agent for the Member States of the European Union, to correct an unsafe condition for certain Agusta Model A109E, A109LUH, A109S, AW109SP, A109C, and A109K2 helicopters. EASA advised of the T/R locking nut loosening on Model A109 helicopters and that one or both of the lock wires securing the locking nut were either damaged or absent from the T/R. EASA states that this condition could lead to failure of the T/R function and subsequent loss of control of the helicopter. AD No. 2012-0195-E requires repetitively inspecting the lock wires and removing and reassembling the housing and slider group of the T/R rotating controls, which is terminating action for the inspections. Actions Since AD 2014-02-08 Was Issued Since we issued AD 2014-02-08 (79 FR 5257, January 31, 2014), a failure of a T/R duplex bearing ring nut installation occurred after the housing and slider group of the T/R rotating controls had been reassembled. Therefore, we are superseding AD 2014-02-08 to remove the reassembly as terminating action. Because of additional reports of the loosening of the bearing locking nut and the increased risk of failure of a lock wire, we are retaining the 25-hour TIS inspection. We are also requiring a daily pilot check to enhance detection of a failure of a T/R duplex bearing ring nut installation. AD 2014-02-18 did not apply to certain serial-numbered helicopters because the terminating action had already been performed on those models. Because we have determined that the terminating action does not correct the unsafe condition, we have expanded the applicability to include all serial-numbered helicopters for the Model A109C, A109S, A109K2, A109E, and AW109SP. EASA has not changed any of the requirements in its AD, and Agusta has not revised its service information. We have also corrected the design holder's name from AgustaWestland S.p.A. to Agusta S.p.A., as specified by the current FAA type certificate. FAA's Determination These helicopters have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We are issuing this AD because we evaluated all known information provided by EASA and determined that an unsafe condition is likely to exist or develop on other helicopters of these same type designs. Related Service Information Agusta issued Bollettino Tecnico (BT) Nos. 109-134, 109EP-121, 109S-48, 109K-54, and 109SP-051, all dated September 21, 2012, for Model A109C, A109E, A109S, A109K2, and AW109SP helicopters. These BTs specify inspecting for the presence and condition of the two locking wires. The BTs also specify if one lock wire is present and no damage is reported, installing a second lock wire. The BTs specify if one or both of the lock wires are damaged, removing and disassembling the housing and slider group of the T/R controls. AD Requirements This AD expands the applicability to include all serial-numbered helicopters. This AD retains the initial and repetitive inspections required by AD 2014-02-08 (79 FR 5257, January 31, 2014) and retains the requirement to remove and reassemble the housing and slider group of the T/R rotating controls if one or both lock wires are damaged. This AD also requires a daily pilot check of each lock wire securing the T/R locking nut. An owner/operator (pilot) may perform the required visual check and must enter compliance with the applicable paragraph of the AD into the helicopter maintenance record in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(1)(2)(v). A pilot may perform this check because it involves only looking at the visible area of the lock wire securing the T/R locking nut to the housing. This check is an exception to our standard maintenance regulations. Differences Between This AD and the EASA AD This AD requires a daily pilot check of the lock wire, while the EASA does not. The EASA AD requires removing and reassembling the housing and slider [[Page 32447]] group of the T/R rotating controls as terminating action, regardless of whether the lock wire is damaged, and this AD does not. The EASA AD applies to certain serial-numbered helicopters, and this AD applies to all serial-numbered helicopters of each model. Interim Action We consider this AD to be an interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this AD affects 122 helicopters of U.S. Registry. We estimate that operators may incur the following costs to comply with this AD. The average labor rate is estimated to be $85 per work-hour. Inspecting the lock wire takes about 0.25 work-hour, and the required parts cost is negligible, for a cost per helicopter of $22 and a total cost to U.S. operators of $2,684 per inspection cycle. Removing and reassembling the housing and slider group of the T/R rotating controls requires about 8 work-hours for a cost per helicopter of $680. FAA's Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to adopting this rule because the previously described unsafe condition can adversely affect the controllability of the helicopter. Since cases of loosening of the T/R duplex bearing locking nut continue to occur, we are requiring a daily pilot check, which must be performed within 24 hours. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in less than 30 days. 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 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 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 removing AD 2014-02-08, Amendment 39- 17736 (79 FR 5257, January 31, 2014), and adding the following new airworthiness directive (AD): 2015-11-08 Agusta S.p.A. Helicopters (Agusta): Docket No. FAA-2015- 1937; Amendment 39-18171, Directorate Identifier 2014-SW-067-AD. (a) Applicability This AD applies to Agusta Model A109C, A109S, A109K2, A109E, and AW109SP helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a missing or broken lock wire securing the tail rotor (T/R) duplex bearing locking nut (locking nut). This condition could result in loosening of the locking nut, failure of the T/R, and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2014-02-08, Amendment 39-17736 (79 FR 5257, January 31, 2014). (d) Comments Due Date We must receive comments by August 10, 2015. (e) 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. (f) Required Actions (1) Within 24 hours and thereafter before the first flight of each day or at intervals not exceeding 24 hours, whichever occurs later, check each lock wire securing the T/R locking nut to the housing. The location of the housing wire is depicted in Figure 1 to paragraph (f)(1) of this AD. BILLING CODE 4910-13-P [[Page 32448]] [GRAPHIC] [TIFF OMITTED] TR09JN15.000 BILLING CODE 4910-13-C (2) The actions required by paragraph (f)(1) may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(1)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (3) Within 5 hours time-in-service (TIS) and thereafter at intervals not to exceed 25 hours TIS, inspect each lock wire securing the T/R locking nut to the housing. (4) If one or both lock wires are missing or damaged, before further flight, remove and reassemble the housing and slider group of the T/R rotating controls. (g) Special Flight Permit Special flight permits are prohibited. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Martin Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email martin.r.crane@faa.gov. (2) 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. (i) Additional Information (1) Agusta Bollettino Tecnico (BT) Nos. 109-134, 109EP-121, 109S-48, 109K-54, and 109SP-051, all dated September 21, 2012, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-664757; fax 39-0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may review a copy of the [[Page 32449]] service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2012-0195-E, dated September 24, 2012, and corrected September 25, 2012. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-1937. (k) Subject Joint Aircraft Service Component (JASC) Code: 6400 Tail Rotor System. Issued in Fort Worth, Texas, on May 26, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-13845 Filed 6-8-15; 8:45 am] BILLING CODE 4910-13-P
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(1) Before the accumulation of 13,875 total Aircraft Certification Office (ACO), 1701 DEPARTMENT OF TRANSPORTATION
flight cycles. Columbia Avenue, College Park, GA 30337;
(2) Within 365 days or 1,000 flight cycles phone: 404–474–5554; fax: 404–474–5605; Federal Aviation Administration
after the effective date of this AD, whichever email: carl.w.gray@faa.gov.
occurs first.
(v) Material Incorporated by Reference
14 CFR Part 39
(p) New Service Information Exception
(1) The Director of the Federal Register [Docket No. FAA–2015–1937; Directorate
If any cracking is found during any Identifier 2014–SW–067–AD; Amendment
inspection required by this AD, and approved the incorporation by reference
39–18171; AD 2015–11–08]
Lockheed Service Bulletin 093–53–105, (IBR) of the service information listed in this
Revision 3, dated May 31, 2013, specifies paragraph under 5 U.S.C. 552(a) and 1 CFR RIN 2120–AA64
contacting Lockheed for appropriate action: part 51.
Before further flight, repair the cracking in (2) You must use this service information Airworthiness Directives; Agusta
accordance with a method approved by the as applicable to do the actions required by S.p.A. (Agusta) Helicopters
Manager, Atlanta ACO, FAA. As of the this AD, unless the AD specifies otherwise.
effective date of this AD, for a repair method AGENCY: Federal Aviation
(3) The following service information was
to be approved by the Manager, Atlanta ACO, approved for IBR on July 14, 2015.
Administration (FAA), DOT.
as required by this paragraph, the Manager’s ACTION: Final rule; request for
(i) Lockheed Service Bulletin 093–53–105,
approval letter must specifically refer to this comments.
AD. Revision 3, dated May 31, 2013 (The date of
May 15, 2013, on page 1 of Lockheed Service
(q) New Pre-Structural Modification Bulletin 093–53–105, Revision 3, dated May
SUMMARY: We are superseding
Inspections and Structural Modification 31, 2013, is incorrect and should be May 31,
airworthiness directive (AD) 2014–02–
Before the accumulation of 20,800 total 2013). 08 for Agusta Model A109C, A109S,
flight cycles: Do the applicable actions (ii) Reserved. A109K2, A109E, and AW109SP
specified in paragraphs (q)(1) and (q)(2) of (4) The following service information was helicopters. AD 2014–02–08 required
this AD. approved for IBR on January 11, 1996 (60 FR inspecting the lock wires securing the
(1) Perform pre-structural modification tail rotor (T/R) duplex bearing locking
66870, December 27, 1995).
inspections by doing the actions required by nut (locking nut) to determine whether
paragraphs (j), (n), and (o) of this AD. (i) Lockheed L–1011 Service Bulletin 093–
53–105, Revision 1, dated November 17, any lock wires are missing or damaged.
(2) Perform a structural modification of the
aft pressure bulkhead by removing and 1995. This AD retains some of the
replacing all stringer end fittings with new or (ii) Reserved. requirements of AD 2014–02–08 but
refurbished fittings at stringers 1 through 14, (5) For Lockheed service information removes the terminating action, expands
and 52 through 64, in accordance with the identified in this AD, contact Lockheed the applicability, and adds a daily pilot
Accomplishment Instructions of Lockheed Martin Corporation/Lockheed Martin check. This AD was prompted by
Service Bulletin 093–53–105, Revision 3, Aeronautics Company, L1011 Technical reports of loosening T/R locking nuts.
dated May 31, 2013. Support Center, Dept. 6A4M, Zone 0579, 86 These actions are intended to prevent
(r) New Post-Structural Modification South Cobb Drive, Marietta, GA 30063–0579; failure of the T/R and subsequent loss
Repetitive Inspections telephone 770–494–5444; fax 770–494–5445; of control of the helicopter.
Within 13,875 flight cycles after email L1011.support@lmco.com; Internet DATES: This AD becomes effective June
performing the actions required by paragraph http://www.lockheedmartin.com/ams/tools/ 24, 2015.
(q)(2) of this AD: Do the actions specified in TechPubs.html. We must receive comments on this
paragraphs (j), (n), and (o) of this AD, and (6) You may view this service information AD by August 10, 2015.
repeat thereafter at intervals not to exceed at FAA, Transport Airplane Directorate, 1601
1,750 flight cycles. ADDRESSES: You may send comments by
Lind Avenue SW., Renton, WA. For
any of the following methods:
(s) No Reporting Requirement information on the availability of this
• Federal eRulemaking Docket: Go to
Although Lockheed Service Bulletin 093– material at the FAA, call 425–227–1221.
http://www.regulations.gov. Follow the
53–105, Revision 3, dated May 31, 2013, (7) You may view this service information
online instructions for sending your
referenced in this AD specifies to submit that is incorporated by reference at the
comments electronically.
certain information to the manufacturer, this National Archives and Records
AD does not include that requirement. Administration (NARA). For information on
• Fax: 202–493–2251.
the availability of this material at NARA, call
• Mail: Send comments to the U.S.
(t) Alternative Methods of Compliance Department of Transportation, Docket
(AMOCs) 202–741–6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr- Operations, M–30, West Building
(1) The Manager, Atlanta ACO, FAA, has Ground Floor, Room W12–140, 1200
locations.html.
the authority to approve AMOCs for this AD, New Jersey Avenue SE., Washington,
if requested using the procedures found in 14 Issued in Renton, Washington, on May 18, DC 20590–0001.
CFR 39.19. In accordance with 14 CFR 39.19, 2015. • Hand Delivery: Deliver to the
send your request to your principal inspector
John P. Piccola, Jr., ‘‘Mail’’ address between 9 a.m. and 5
or local Flight Standards District Office, as
appropriate. If sending information directly Acting Manager, Transport Airplane p.m., Monday through Friday, except
to the manager of the ACO, send it to the Directorate, Aircraft Certification Service. Federal holidays.
attention of the person identified in [FR Doc. 2015–13325 Filed 6–8–15; 8:45 am]
Examining the AD Docket
paragraph (u) of this AD. BILLING CODE 4910–13–P
(2) Before using any approved AMOC, You may examine the AD docket on
notify your appropriate principal inspector, the Internet at http://
or lacking a principal inspector, the manager www.regulations.gov or in person at the
tkelley on DSK3SPTVN1PROD with RULES
of the local flight standards district office/ Docket Operations Office between 9
certificate holding district office.
a.m. and 5 p.m., Monday through
(u) Related Information Friday, except Federal holidays. The AD
For more information about this AD, docket contains this AD, the European
contact Carl Gray, Aerospace Engineer, Aviation Safety Agency (EASA) AD, the
Airframe Branch, ACE–117A, FAA, Atlanta economic evaluation, any comments
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group of the T/R rotating controls as Authority for This Rulemaking Adoption of the Amendment
terminating action, regardless of Title 49 of the United States Code Accordingly, under the authority
whether the lock wire is damaged, and specifies the FAA’s authority to issue delegated to me by the Administrator,
this AD does not. The EASA AD applies rules on aviation safety. Subtitle I, the FAA amends 14 CFR part 39 as
to certain serial-numbered helicopters, section 106, describes the authority of follows:
and this AD applies to all serial- the FAA Administrator. ‘‘Subtitle VII:
numbered helicopters of each model. Aviation Programs,’’ describes in more PART 39—AIRWORTHINESS
Interim Action detail the scope of the Agency’s DIRECTIVES
authority.
We consider this AD to be an interim We are issuing this rulemaking under ■ 1. The authority citation for part 39
action. If final action is later identified, the authority described in ‘‘Subtitle VII, continues to read as follows:
we might consider further rulemaking Part A, Subpart III, Section 44701: Authority: 49 U.S.C. 106(g), 40113, 44701.
then. General requirements.’’ Under that
§ 39.13 [Amended]
Costs of Compliance section, Congress charges the FAA with
promoting safe flight of civil aircraft in ■ 2. The FAA amends § 39.13 by
We estimate that this AD affects 122 air commerce by prescribing regulations removing AD 2014–02–08, Amendment
helicopters of U.S. Registry. We estimate for practices, methods, and procedures 39–17736 (79 FR 5257, January 31,
that operators may incur the following the Administrator finds necessary for 2014), and adding the following new
costs to comply with this AD. The safety in air commerce. This regulation airworthiness directive (AD):
average labor rate is estimated to be $85 is within the scope of that authority 2015–11–08 Agusta S.p.A. Helicopters
per work-hour. Inspecting the lock wire because it addresses an unsafe condition (Agusta): Docket No. FAA–2015–1937;
takes about 0.25 work-hour, and the that is likely to exist or develop on Amendment 39–18171, Directorate
required parts cost is negligible, for a products identified in this rulemaking Identifier 2014–SW–067–AD.
cost per helicopter of $22 and a total action. (a) Applicability
cost to U.S. operators of $2,684 per Regulatory Findings This AD applies to Agusta Model A109C,
inspection cycle. Removing and A109S, A109K2, A109E, and AW109SP
reassembling the housing and slider We determined that this AD will not
helicopters, certificated in any category.
group of the T/R rotating controls have federalism implications under
requires about 8 work-hours for a cost Executive Order 13132. This AD will (b) Unsafe Condition
per helicopter of $680. not have a substantial direct effect on This AD defines the unsafe condition as a
the States, on the relationship between missing or broken lock wire securing the tail
FAA’s Justification and Determination the national Government and the States, rotor (T/R) duplex bearing locking nut
of the Effective Date or on the distribution of power and (locking nut). This condition could result in
responsibilities among the various loosening of the locking nut, failure of the
Providing an opportunity for public T/R, and subsequent loss of control of the
comments prior to adopting these AD levels of government.
helicopter.
For the reasons discussed, I certify
requirements would delay
that this AD: (c) Affected ADs
implementing the safety actions needed
1. Is not a ‘‘significant regulatory This AD supersedes AD 2014–02–08,
to correct this known unsafe condition.
action’’ under Executive Order 12866; Amendment 39–17736 (79 FR 5257, January
Therefore, we find that the risk to the
2. Is not a ‘‘significant rule’’ under 31, 2014).
flying public justifies waiving notice
DOT Regulatory Policies and Procedures (d) Comments Due Date
and comment prior to adopting this rule
(44 FR 11034, February 26, 1979);
because the previously described unsafe We must receive comments by August 10,
3. Will not affect intrastate aviation in
condition can adversely affect the 2015.
Alaska to the extent that it justifies
controllability of the helicopter. Since
making a regulatory distinction; and (e) Compliance
cases of loosening of the T/R duplex 4. Will not have a significant
bearing locking nut continue to occur, You are responsible for performing each
economic impact, positive or negative, action required by this AD within the
we are requiring a daily pilot check, on a substantial number of small entities specified compliance time unless it has
which must be performed within 24 under the criteria of the Regulatory already been accomplished prior to that time.
hours. Flexibility Act. (f) Required Actions
Since an unsafe condition exists that We prepared an economic evaluation
requires the immediate adoption of this (1) Within 24 hours and thereafter before
of the estimated costs to comply with the first flight of each day or at intervals not
AD, we determined that notice and this AD and placed it in the AD docket. exceeding 24 hours, whichever occurs later,
opportunity for public comment before check each lock wire securing the T/R
issuing this AD are impracticable and List of Subjects in 14 CFR Part 39
locking nut to the housing. The location of
that good cause exists for making this Air transportation, Aircraft, Aviation the housing wire is depicted in Figure 1 to
amendment effective in less than 30 safety, Incorporation by reference, paragraph (f)(1) of this AD.
days. Safety. BILLING CODE 4910–13–P
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service information at the FAA, Office of the www.regulations.gov/ extend the MLG into the down and locked
Regional Counsel, Southwest Region, 2601 #!docketDetail;D=FAA-2014-0754; or in position, resulting in an unsafe landing
Meacham Blvd., Room 663, Fort Worth, person at the Docket Management configuration.
Texas 76137. Facility, U.S. Department of This [Canadian] AD mandates the [general
(2) The subject of this AD is addressed in visual] inspection of the MLG alternate
European Aviation Safety Agency (EASA) AD
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room extension system reservoir lid for correct
No. 2012–0195–E, dated September 24, 2012, assembly and the required rectification [i.e.,
and corrected September 25, 2012. You may W12–140, 1200 New Jersey Avenue SE., corrective action which consists of repairing
view the EASA AD on the Internet at Washington, DC. the lid assembly].
http://www.regulations.gov in Docket No. For Bombardier service information
FAA–2015–1937. identified in this AD, contact You may examine the MCAI in the
Bombardier, Inc., Q-Series Technical AD docket on the Internet at http://
(k) Subject www.regulations.gov/
Help Desk, 123 Garratt Boulevard,
Joint Aircraft Service Component (JASC) #!documentDetail;D=FAA-2014-0754-
Toronto, Ontario M3K 1Y5, Canada;
Code: 6400 Tail Rotor System. 0002.
telephone 416–375–4000; fax 416–375–
Issued in Fort Worth, Texas, on May 26, 4539; email thd.qseries@
2015.
Comments
aero.bombardier.com; Internet http://
Lance T. Gant, www.bombardier.com. For Parker We gave the public the opportunity to
Acting Directorate Manager, Rotorcraft service information identified in this participate in developing this AD. We
Directorate, Aircraft Certification Service. AD, contact Parker Aerospace, 14300 received no comments on the NPRM (79
[FR Doc. 2015–13845 Filed 6–8–15; 8:45 am] Alton Parkway, Irvine, CA 92618; FR 63341, October 23, 2014) or on the
BILLING CODE 4910–13–P phone: 949–833–3000; Internet: http:// determination of the cost to the public.
www.parker.com. You may view this Conclusion
referenced service information at the
DEPARTMENT OF TRANSPORTATION We reviewed the relevant data and
FAA, Transport Airplane Directorate,
determined that air safety and the
1601 Lind Avenue SW., Renton, WA.
Federal Aviation Administration public interest require adopting this AD
For information on the availability of
as proposed except for minor editorial
this material at the FAA, call 425–227–
14 CFR Part 39 changes. We have determined that these
1221. It is also available on the Internet
minor changes:
[Docket No. FAA–2014–0754; Directorate at http://www.regulations.gov by
• Are consistent with the intent that
Identifier 2014–NM–136–AD; Amendment searching for and locating Docket No.
39–18156; AD 2015–10–01] was proposed in the NPRM (79 FR
FAA–2014–0754.
63341, October 23, 2014) for correcting
RIN 2120–AA64 FOR FURTHER INFORMATION CONTACT:
the unsafe condition; and
Fabio Buttitta, Aerospace Engineer, • Do not add any additional burden
Airworthiness Directives; Bombardier, Airframe and Mechanical Systems upon the public than was already
Inc. Airplanes Branch, ANE–171, FAA, New York proposed in the NPRM (79 FR 63341,
Aircraft Certification Office (ACO), 1600 October 23, 2014).
AGENCY: Federal Aviation Stewart Avenue, Suite 410, Westbury,
Administration (FAA), Department of NY 11590; telephone 516–228–7303; fax Related Service Information Under 1
Transportation (DOT). 516–794–5531. CFR Part 51
ACTION: Final rule. SUPPLEMENTARY INFORMATION: Bombardier has issued Service
SUMMARY: We are adopting a new Discussion Bulletin 84–29–34, dated May 9, 2013,
airworthiness directive (AD) for certain with the attached Parker Service
We issued a notice of proposed Bulletin 82910012–29–431, dated
Bombardier, Inc. Model DHC–8–400 rulemaking (NPRM) to amend 14 CFR
series airplanes. This AD was prompted October 22, 2012. This service
part 39 by adding an AD that would information describes procedures to
by reports of hydraulic fluid loss from apply to certain Bombardier, Inc. Model
the reservoir of the main landing gear inspect the lid assembly of the MLG
DHC–8–400 series airplanes. The NPRM alternate extension system reservoir for
(MLG) alternate extension system. This published in the Federal Register on
AD requires inspection for correct correct assembly and corrective actions.
October 23, 2014 (79 FR 63341). This service information is reasonably
assembly of the MLG alternate extension Transport Canada Civil Aviation
system reservoir lid, and corrective available because the interested parties
(TCCA), which is the aviation authority have access to it through their normal
action if necessary. We are issuing this for Canada, has issued Canadian
AD to, in the event of a failure of the course of business or by the means
Airworthiness Directive CF–2014–15, identified in the ADDRESSES section of
primary MLG extension system, prevent dated June 6, 2014 (referred to after this
failure of the alternate MLG extension this AD.
as the Mandatory Continuing
system to fully extend the MLG into a Airworthiness Information, or ‘‘the Costs of Compliance
down-and-locked position, which could MCAI’’), to correct an unsafe condition
result in collapse of both left-hand and We estimate that this AD affects 173
for certain Bombardier, Inc. Model airplanes of U.S. registry.
right-hand MLG sides during DHC–8–400 series airplanes. The MCAI
touchdown. We also estimate that it will take
states: about 4 work-hours per product to
DATES: This AD becomes effective July Several cases have been reported of hydraulic comply with the basic requirements of
14, 2015. fluid loss from the main landing gear (MLG) this AD. The average labor rate is $85
tkelley on DSK3SPTVN1PROD with RULES
The Director of the Federal Register alternate extension system reservoir and in per work-hour. Based on these figures,
approved the incorporation by reference one case, the reservoir was found empty. The
we estimate the cost of this AD on U.S.
of a certain publication listed in this AD cause was determined to be an incorrectly
assembled reservoir lid. In the event of a operators to be $58,820, or $340 per
as of July 14, 2015. failed primary MLG extension system, an product.
ADDRESSES: You may examine the AD alternate MLG extension system with an In addition, we estimate that any
docket on the Internet at http:// empty reservoir may not be able to fully necessary follow-on actions will take
VerDate Sep<11>2014 15:56 Jun 08, 2015 Jkt 235001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\09JNR1.SGM 09JNR1](https://thefederalregister.org/doc/80_FR_32555/page/5.svg)
Document Created: 2015-12-15 15:25:28
Document Modified: 2015-12-15 15:25:28
| 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 | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective June 24, 2015. | |
| Contact | Martin Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 80 FR 32445 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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