81 FR 40203 - Airworthiness Directives; Airbus Helicopters Deutschland GmbH
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 119 (June 21, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 119 (June 21, 2016)
| Page Range | 40203-40205 | |
| FR Document | 2016-14470 |
[Federal Register Volume 81, Number 119 (Tuesday, June 21, 2016)] [Proposed Rules] [Pages 40203-40205] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-14470] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7415; Directorate Identifier 2015-SW-076-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters. This proposed AD would require repetitive visual inspections and a one-time torque of each hydraulic module plate assembly attachment point (attachment point). This proposed AD is prompted by a design reassessment showing the current attachment point design is insufficient in preventing an attachment point failure. The proposed actions are intended to prevent failure of an attachment point, loss of the hydraulic module plate, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by August 22, 2016. 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-2016- 7415; 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 European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other [[Page 40204]] 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 rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub. 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: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 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 expense or delay. We may change this proposal in light of the comments we receive. Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2015-0210R1, Revision 1, dated October 28, 2015, to correct an unsafe condition for Airbus Helicopters Model MBB-BK117 C-2, MBB-BK117 C-2e, MBB-BK117 D-2, and MBB-BK117 D-2m helicopters. EASA advises that the hydraulic plate assembly on certain MBB-BK117 models has four attachment points on the fuselage secured by a single locking mechanism. According to EASA, a design reassessment revealed stiffness of the hydraulic plate may be insufficient in the event one of the four single locking attachment points fails. EASA states that if this condition is not detected and corrected, it may lead to loss of the hydraulic module plate and possible loss of control of the helicopter. Therefore, the EASA AD requires a repetitive inspection and one-time torque tightening of the attachment points in accordance with Airbus Helicopters' service information. EASA considers its AD an interim action and states further AD action may follow. FAA's Determination These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003 and Airbus Helicopters ASB No. ASB MBB-BK117 D-2- 29A-001, both Revision 0, and both dated October 12, 2015. This service information specifies a repetitive visual inspection for condition and correct installation of the attachment points, and if there is a crack, replacing the affected parts and contacting Airbus Helicopters customer support. This service information also specifies a tightening torque check after the initial inspection and, if torque cannot be applied, replacing the affected parts and contacting Airbus Helicopters customer support. 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, within 100 hours time-in-service (TIS) and thereafter at intervals not to exceed 400 hours TIS, performing a visual inspection of each attachment point of the hydraulic module plate assembly for a crack and proper installation. This proposed AD would also require, within 100 hours TIS, applying torque to the nuts of each attachment point. Differences Between This Proposed AD and the EASA AD The EASA AD requires contacting Airbus Helicopters customer support when replacing affected parts, and this proposed AD would not. Interim Action We consider this proposed AD to be an interim action. Airbus Helicopters is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. Costs of Compliance We estimate that this proposed AD would affect 134 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. We estimate the cost of labor at $85 per work-hour. Visually inspecting the four attachment points would take about 0.75 work-hour for an estimated cost of $64 per helicopter and $8,576 for the U.S. fleet per inspection cycle. Inspecting the torque of the four attachment points would take about 0.25 work-hour an estimated cost of $21 per helicopter and $2,814 for the U.S. fleet. Replacing any of the attachment point parts would take a minimal amount of time and parts would cost about $48 per attachment point. 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. [[Page 40205]] 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 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 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): Airbus Helicopters Deutschland GmbH: Docket No. FAA-2016-7415; Directorate Identifier 2015-SW-076-AD. (a) Applicability This AD applies to Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters with a hydraulic module plate assembly part number B291M0003103 with a single locking attachment point installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as failure of a hydraulic module plate assembly attachment point (attachment point). This condition could result in loss of the hydraulic module plate and subsequent loss of control of the helicopter. (c) Comments Due Date We must receive comments by August 22, 2016. (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) Within 100 hours time-in-service (TIS): (i) Visually inspect the split pins, castellated nuts, plugs, nuts, and hexagon bolts of each attachment point for a crack and for proper installation by following the Accomplishment Instructions, paragraphs 3.B.1.2.a. through 3.B.1.2.e., of Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003, Revision 0, dated October 12, 2015 (ASB MBB-BK117 C-2-29A-003), or Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, Revision 0, dated October 12, 2015 (ASB MBB-BK117 D-2-29A-001), as applicable to your model helicopter. Replace any part that has a crack before further flight. If the split pins, castellated nuts, or hexagon bolts are not as depicted in Figure 2 of ASB MBB-BK117 C-2-29A-003 or ASB MBB- BK117 D-2-29A-001, before further flight, properly install them. (ii) Apply a torque of 9 to 10 Nm to the left-hand and right- hand nuts of each attachment point. If a torque of 9 to 10 Nm cannot be applied, replace the affected nut before further flight. (2) Thereafter, at intervals not to exceed 400 hours TIS, perform the inspection in paragraph (e)(1)(i) of this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]. (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. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015-0210R1, Revision 1, dated October 28, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in the AD Docket. (h) Subject Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic Power System. Issued in Fort Worth, Texas, on June 9, 2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-14470 Filed 6-20-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Proposed Rules 40203
was used, in accordance with the any approved AMOC, notify your appropriate DEPARTMENT OF TRANSPORTATION
Accomplishment Instructions of the principal inspector, or lacking a principal
applicable service information identified in inspector, the manager of the local flight Federal Aviation Administration
paragraphs (g)(1), (g)(2), and (g)(3) of this AD. standards district office/certificate holding
(1) For cargo compartment structural parts district office. The AMOC approval letter
for Model A330 airplanes: Airbus Service
14 CFR Part 39
must specifically reference this AD.
Bulletin A330–53–3261, including [Docket No. FAA–2016–7415; Directorate
Appendixes 01, 02, and 03, dated June 23, (2) Contacting the Manufacturer: For any
Identifier 2015–SW–076–AD]
2015. requirement in this AD to obtain corrective
(2) For cabin structural parts for Model actions from a manufacturer, the action must RIN 2120–AA64
A330 airplanes: Airbus Service Bulletin be accomplished using a method approved
A330–53–3262, including Appendixes 01 by the Manager, International Branch, ANM– Airworthiness Directives; Airbus
and 02, dated June 23, 2015. 116, Transport Airplane Directorate, FAA; or Helicopters Deutschland GmbH
(3) For cargo compartment structural parts the European Aviation Safety Agency
for Model A340 airplanes: Airbus Service AGENCY: Federal Aviation
(EASA); or Airbus’s EASA Design
Bulletin A340–53–5072, including Administration (FAA), DOT.
Organization Approval (DOA). If approved by
Appendixes 01 and 02, dated June 23, 2015. ACTION: Notice of proposed rulemaking
the DOA, the approval must include the
DOA-authorized signature. (NPRM).
TABLE 1 TO PARAGRAPHS (g) AND (h) (3) Required for Compliance (RC): If any
OF THIS AD—PARTS TO BE IN- SUMMARY: We propose to adopt a new
service information contains procedures or
SPECTED/INSTALLED
airworthiness directive (AD) for Airbus
tests that are identified as RC, those
Helicopters Deutschland GmbH (Airbus
procedures and tests must be done to comply
Acceptable Helicopters) Model MBB–BK 117 C–2
with this AD; any procedures or tests that are
Affected part No. replacement Area and MBB–BK 117 D–2 helicopters. This
part No. not identified as RC are recommended. Those
proposed AD would require repetitive
procedures and tests that are not identified
visual inspections and a one-time torque
F5347126620600 F5347126620000 Cabin as RC may be deviated from using accepted
methods in accordance with the operator’s
of each hydraulic module plate
F5347126621000 F5347126620400 Cabin
F5347170420400 F5347170420400 Cargo maintenance or inspection program without
assembly attachment point (attachment
F5347170420600 F5347170420600 Cargo obtaining approval of an AMOC, provided point). This proposed AD is prompted
F5377004320300 F5377004320051 Cargo the procedures and tests identified as RC can by a design reassessment showing the
F5397096620200 F5397096620200 Cargo be done and the airplane can be put back in current attachment point design is
G5367131300000 G5367131300000 Cargo an airworthy condition. Any substitutions or insufficient in preventing an attachment
G5367173700000 G5367173700000 Cargo changes to procedures or tests identified as point failure. The proposed actions are
G5367173800000 G5367173800000 Cargo intended to prevent failure of an
RC require approval of an AMOC.
attachment point, loss of the hydraulic
(h) Replacement (j) Related Information module plate, and subsequent loss of
If during the inspection required by (1) Refer to Mandatory Continuing control of the helicopter.
paragraph (g) of this AD, any affected part Airworthiness Information (MCAI) EASA DATES: We must receive comments on
having a part number specified in table 1 to Airworthiness Directive 2015–0206, dated this proposed AD by August 22, 2016.
paragraphs (g) and (h) of this AD is found to October 12, 2015, for related information.
have a measured value greater than that ADDRESSES: You may send comments by
This MCAI may be found in the AD docket
specified in Figure A–GFAAA, Sheet 02, any of the following methods:
on the Internet at http://www.regulations.gov
‘‘Inspection Flowchart,’’ of the applicable • Federal eRulemaking Docket: Go to
service information identified in paragraphs by searching for and locating Docket No.
http://www.regulations.gov. Follow the
(g)(1), (g)(2), and (g)(3) of this AD: Before FAA–2016–7264.
online instructions for sending your
further flight, replace with an acceptable (2) For service information identified in
comments electronically.
replacement part having a part number this AD, contact Airbus SAS, Airworthiness
• Fax: 202–493–2251.
specified in table 1 to paragraphs (g) and (h) Office—EAL, 1 Rond Point Maurice Bellonte,
of this AD, in accordance with the
• Mail: Send comments to the U.S.
31707 Blagnac Cedex, France; telephone +33
Accomplishment Instructions of the Department of Transportation, Docket
5 61 93 36 96; fax +33 5 61 93 45 80; email
applicable service information identified in airworthiness.A330-A340@airbus.com;
Operations, M–30, West Building
paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Internet http://www.airbus.com. You may
Ground Floor, Room W12–140, 1200
view this service information at the FAA,
New Jersey Avenue SE., Washington,
(i) Other FAA AD Provisions
Transport Airplane Directorate, 1601 Lind DC 20590–0001.
The following provisions also apply to this
Avenue SW., Renton, WA. For information • Hand Delivery: Deliver to the
AD: ‘‘Mail’’ address between 9 a.m. and 5
(1) Alternative Methods of Compliance on the availability of this material at the
FAA, call 425–227–1221. p.m., Monday through Friday, except
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane Federal holidays.
Issued in Renton, Washington, on June 9,
Directorate, FAA, has the authority to Examining the AD Docket
2016.
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Michael Kaszycki, You may examine the AD docket on
In accordance with 14 CFR 39.19, send your Acting Manager, Transport Airplane the Internet at http://
request to your principal inspector or local Directorate, Aircraft Certification Service. www.regulations.gov by searching for
Flight Standards District Office, as [FR Doc. 2016–14430 Filed 6–20–16; 8:45 am] and locating Docket No. FAA–2016–
rmajette on DSK2TPTVN1PROD with PROPOSALS
appropriate. If sending information directly 7415; or in person at the Docket
to the International Branch, send it to ATTN: BILLING CODE 4910–13–P
Operations Office between 9 a.m. and 5
Vladimir Ulyanov, Aerospace Engineer,
p.m., Monday through Friday, except
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind Federal holidays. The AD docket
Avenue SW., Renton, WA 98057–3356; contains this proposed AD, the
telephone 425–227–1138; fax 425–227–1149. European Aviation Safety Agency
Information may be emailed to: 9-ANM-116- (EASA) AD, the economic evaluation,
AMOC-REQUESTS@faa.gov. Before using any comments received, and other
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Regulatory Findings hydraulic module plate and subsequent loss Issued in Fort Worth, Texas, on June 9,
of control of the helicopter. 2016.
We determined that this proposed AD
(c) Comments Due Date Scott A. Horn,
would not have federalism implications
under Executive Order 13132. This Acting Manager, Rotorcraft Directorate,
We must receive comments by August 22,
Aircraft Certification Service.
proposed AD would not have a 2016.
[FR Doc. 2016–14470 Filed 6–20–16; 8:45 am]
substantial direct effect on the States, on (d) Compliance
the relationship between the national BILLING CODE 4910–13–P
Government and the States, or on the You are responsible for performing each
action required by this AD within the
distribution of power and
specified compliance time unless it has DEPARTMENT OF TRANSPORTATION
responsibilities among the various already been accomplished prior to that time.
levels of government. Federal Aviation Administration
For the reasons discussed, I certify (e) Required Actions
this proposed regulation: (1) Within 100 hours time-in-service (TIS): 14 CFR Part 39
1. Is not a ‘‘significant regulatory (i) Visually inspect the split pins,
action’’ under Executive Order 12866; castellated nuts, plugs, nuts, and hexagon [Docket No. FAA–2016–7261; Directorate
2. Is not a ‘‘significant rule’’ under the bolts of each attachment point for a crack and Identifier 2016–NM–004–AD]
DOT Regulatory Policies and Procedures for proper installation by following the
RIN 2120–AA64
(44 FR 11034, February 26, 1979); Accomplishment Instructions, paragraphs
3. Will not affect intrastate aviation in 3.B.1.2.a. through 3.B.1.2.e., of Airbus Airworthiness Directives; The Boeing
Helicopters Alert Service Bulletin (ASB) No.
Alaska to the extent that it justifies Company Airplanes
ASB MBB–BK117 C–2–29A–003, Revision 0,
making a regulatory distinction; and dated October 12, 2015 (ASB MBB–BK117 C–
4. Will not have a significant AGENCY: Federal Aviation
2–29A–003), or Airbus Helicopters ASB No. Administration (FAA), DOT.
economic impact, positive or negative, ASB MBB–BK117 D–2–29A–001, Revision 0,
on a substantial number of small entities ACTION: Notice of proposed rulemaking
dated October 12, 2015 (ASB MBB–BK117 D–
under the criteria of the Regulatory 2–29A–001), as applicable to your model (NPRM).
Flexibility Act. helicopter. Replace any part that has a crack
SUMMARY: We propose to adopt a new
We prepared an economic evaluation before further flight. If the split pins,
castellated nuts, or hexagon bolts are not as airworthiness directive (AD) for certain
of the estimated costs to comply with
depicted in Figure 2 of ASB MBB–BK117 C– The Boeing Company Model 747–200B,
this proposed AD and placed it in the
2–29A–003 or ASB MBB–BK117 D–2–29A– 747–300, 747–400, 747–400D, and 747–
AD docket.
001, before further flight, properly install 400F series airplanes. This proposed AD
List of Subjects in 14 CFR Part 39 them. was prompted by a report of cracking in
Air transportation, Aircraft, Aviation (ii) Apply a torque of 9 to 10 Nm to the both the aluminum strut side skin, and
left-hand and right-hand nuts of each corrosion resistant steel (CRES) outer
safety, Incorporation by reference, attachment point. If a torque of 9 to 10 Nm
Safety. spring beam support fitting. This
cannot be applied, replace the affected nut proposed AD would require repetitive
The Proposed Amendment before further flight. high frequency eddy current (HFEC)
(2) Thereafter, at intervals not to exceed
Accordingly, under the authority inspections for cracking in the strut side
400 hours TIS, perform the inspection in
delegated to me by the Administrator, paragraph (e)(1)(i) of this AD.
skin; an open-hole HFEC inspection for
the FAA proposes to amend 14 CFR part cracking, applicable related
(f) Alternative Methods of Compliance investigative and corrective actions; and
39 as follows:
(AMOCs) a fastener installation modification. We
PART 39—AIRWORTHINESS (1) The Manager, Safety Management are proposing this AD to detect and
DIRECTIVES Group, FAA, may approve AMOCs for this correct cracking of the strut side skin;
AD. Send your proposal to: Matt Fuller, such cracking could result in the failure
■ 1. The authority citation for part 39 Senior Aviation Safety Engineer, Safety of the outer spring beam support fitting,
continues to read as follows: Management Group, Rotorcraft Directorate, which could cause separation of a strut
FAA, 10101 Hillwood Pkwy., Fort Worth, TX
Authority: 49 U.S.C. 106(g), 40113, 44701. and engine from the airplane during
76177; telephone (817) 222–5110; email 9-
ASW-FTW-AMOC-Requests@faa.gov.
flight.
§ 39.13 [Amended]
(2) For operations conducted under a 14 DATES: We must receive comments on
■ 2. The FAA amends § 39.13 by adding CFR part 119 operating certificate or under this proposed AD by August 5, 2016.
the following new airworthiness 14 CFR part 91, subpart K, we suggest that ADDRESSES: You may send comments,
directive (AD): you notify your principal inspector, or
using the procedures found in 14 CFR
Airbus Helicopters Deutschland GmbH: lacking a principal inspector, the manager of
the local flight standards district office or 11.43 and 11.45, by any of the following
Docket No. FAA–2016–7415; Directorate methods:
Identifier 2015–SW–076–AD. certificate holding district office before
operating any aircraft complying with this • Federal eRulemaking Portal: Go to
(a) Applicability AD through an AMOC. http://www.regulations.gov. Follow the
This AD applies to Model MBB–BK 117 C– instructions for submitting comments.
(g) Additional Information • Fax: 202–493–2251.
2 and MBB–BK 117 D–2 helicopters with a
hydraulic module plate assembly part The subject of this AD is addressed in • Mail: U.S. Department of
rmajette on DSK2TPTVN1PROD with PROPOSALS
number B291M0003103 with a single locking European Aviation Safety Agency (EASA) AD Transportation, Docket Operations, M–
attachment point installed, certificated in any No. 2015–0210R1, Revision 1, dated October 30, West Building Ground Floor, Room
category. 28, 2015. You may view the EASA AD on the W12–140, 1200 New Jersey Avenue SE.,
Internet at http://www.regulations.gov in the
(b) Unsafe Condition Washington, DC 20590.
AD Docket.
This AD defines the unsafe condition as • Hand Delivery: Deliver to Mail
failure of a hydraulic module plate assembly (h) Subject address above between 9 a.m. and 5
attachment point (attachment point). This Joint Aircraft Service Component (JASC) p.m., Monday through Friday, except
condition could result in loss of the Code: 2900, Hydraulic Power System. Federal holidays.
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Document Created: 2016-06-21 01:30:43
Document Modified: 2016-06-21 01:30:43
| 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 August 22, 2016. | |
| Contact | Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 81 FR 40203 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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