81 FR 74285 - Airworthiness Directives; Bell Helicopter Textron
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 207 (October 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 207 (October 26, 2016)
| Page Range | 74285-74287 | |
| FR Document | 2016-25742 |
[Federal Register Volume 81, Number 207 (Wednesday, October 26, 2016)] [Rules and Regulations] [Pages 74285-74287] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-25742] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3821; Directorate Identifier 2014-SW-025-AD; Amendment 39-18696; AD 2016-22-07] RIN 2120-AA64 Airworthiness Directives; Bell Helicopter Textron AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 75-26-05 for Bell Helicopter Textron (Bell) Model 204B, 205A-1 and 212 helicopters. AD 75-26-05 required removing and visually inspecting each main rotor (M/R) blade and, depending on the inspection's outcome, repairing or replacing the M/R blades. This new AD requires more frequent inspections of certain M/R blades and applies to Model 205A helicopters. This AD does not require that helicopter blades be removed to conduct the initial visual inspections. We are issuing this AD to detect a crack and prevent failure of an M/R blade and subsequent loss of helicopter control. DATES: This AD is effective November 30, 2016. ADDRESSES: For service information identified in this final rule, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov in Docket No. FAA-2015-3821; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647-5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5140; email [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975) and add a new AD. AD 75-26-05 applied to Bell Model 204B, 205A-1, and 212 helicopters. AD 75-26-05 required removing and visually inspecting each M/R blade and, depending on the inspection's outcome, repairing or replacing the M/R blade. The NPRM published in the Federal Register on May 5, 2016 (81 FR 27055). The NPRM was prompted by a report of an M/R blade with multiple fatigue cracks around the retention bolt hole. The NPRM proposed to require more frequent inspections of certain M/R blades and proposed to remove the requirement that helicopter blades be removed to conduct the initial visual inspections. The NPRM also proposed to include the Model 205A in the applicability but remove the Model 212 because similar inspections are required by AD 2011-23-02 (76 FR 68301, November 4, 2011). Finally, the NPRM included specific part-numbered blades in the applicability so that the proposed AD would no longer be required if a new blade is designed that is not subject to the unsafe condition. Comments We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (81 FR 27055, May 5, 2016). FAA's Determination We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Related Service Information Bell issued Alert Service Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013, for the Model UH-1H helicopter (ASB UH-1H-13-09). ASB UH-1H-13-09 specifies a one-time visual inspection, within 10 hours time-in-service (TIS), of the lower grip pad and upper and lower grip plates for cracks, edge voids, and loose or damaged adhesive squeeze- out. ASB UH-1H-13-09 also specifies a repetitive visual inspection, daily and at every 150 hours TIS of the lower grip pad, upper and lower grip plates, and all upper and the lower doublers for cracks, corrosion, edge voids, and loose or damaged adhesive squeeze-out. Similar inspections are contained in Bell ASB No. 204-75-1 (ASB 204-75- 1) and No. 205-75-5 (ASB 205-75-5), both Revision C and both dated April 25, 1979, for Bell Model 204B and 205A-1 helicopters, respectively. ASB 204-75-1 and ASB 205-75-5 call for daily inspections and for inspections, rework, and refinishing every 1,000 hours TIS or 12 months, whichever occurs first. Differences Between This AD and the Service Information This AD requires all inspections every 25 hours TIS or 2 weeks, whichever occurs first. ASB UH-1H-13-09 specifies a one-time inspection within 10 hours TIS, and then a second repetitive inspection daily and at every 150 hours TIS, while ASB 204-75-1 and ASB 205-75-5 call for daily visual inspections, and inspections, rework, and refinishing every 1,000 hours TIS or 12 months, whichever occurs first. This AD contains more detailed inspection requirements and a more specific inspection area than the instructions in ASB UH-1H-13-09. The service information applies to M/R blade, part number (P/N) 204-011-250, and was issued for Model 204B and 205A-1 helicopters. This AD also applies to P/N 204-011-200 because this blade is of the same type and susceptible to the unsafe condition. This AD also applies [[Page 74286]] to certain M/R blades installed on the Model 205A helicopters. While none of these models are registered in the U.S., they were included because of blade P/N eligibility. Costs of Compliance We estimate that this AD affects 52 helicopters of U.S. Registry and that labor costs average $85 a work-hour. Based on these estimates, we expect the following costs: Cleaning and performing all inspections of a set of M/R blades (2 per helicopter) requires a half work-hour. No parts are needed. At an estimated 24 inspections a year, the cost is $1,032 per helicopter and $53,664 for the U.S. fleet. Replacing an M/R blade requires 12 work hours and parts cost $90,656 for a total cost of $91,676 per blade. 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 have 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 above, 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 a regulatory distinction is required and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 Airworthiness Directive (AD) 75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975), and adding the following new AD: 2016-22-07 Bell Helicopter Textron: Amendment 39-18696; Docket No. FAA-2015-3821; Directorate Identifier 2014-SW-025-AD. (a) Applicability This AD applies to Model 204B, 205A, and 205A-1 helicopters with a main rotor (M/R) blade, part number (P/N) 204-011-200-001 or P/N 204-011-250-(all dash numbers), installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in an M/R blade, which could result in failure of an M/R blade and subsequent loss of helicopter control. (c) Affected ADs This AD supersedes AD 75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975). (d) Effective Date This AD becomes effective November 30, 2016. (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 25 hours time-in-service (TIS) or 2 weeks, whichever occurs first, and thereafter at intervals not to exceed 25 hours TIS or 2 weeks, whichever occurs first, clean the upper and lower exposed surfaces of each M/R blade from an area starting at the butt end of the blade to three inches outboard of the doublers. Using a 3X or higher power magnifying glass and a light, inspect as follows: (i) Visually inspect the exposed areas of the lower grip pad and upper and lower grip plates of each M/R blade for a crack and any corrosion. (ii) On the upper and lower exposed surfaces of each M/R blade from blade stations 24.5 to 35 for the chord width, visually inspect each layered doubler and blade skin for a crack and any corrosion. Pay particular attention for any cracking in a doubler or skin near or at the same blade station as the blade retention bolt hole (blade station 28). (iii) Visually inspect the exposed areas of each bond line at the edges of the lower grip pad, upper and lower grip plates, and each layered doubler (bond lines) on the upper and lower surfaces of each M/R blade for the entire length and chord width for an edge void, any corrosion, loose or damaged adhesive squeeze-out, and an edge delamination. Pay particular attention to any crack in the paint finish that follows the outline of a grip pad, grip plate, or doubler, and to any loose or damaged adhesive squeeze-out, as these may be the indication of an edge void. (2) If there is a crack, any corrosion, an edge void, loose or damaged adhesive squeeze-out, or an edge delamination during any inspection in paragraph (f)(1) of this AD, before further flight, do the following: (i) If there is a crack in a grip pad or any grip plate or doubler, replace the M/R blade with an airworthy M/R blade. (ii) If there is a crack in the M/R blade skin that is within maximum repair damage limits, repair the M/R blade. If the crack exceeds maximum repair damage limits, replace the M/R blade with an airworthy M/R blade. (iii) If there is any corrosion within maximum repair damage limits, repair the M/R blade. If the corrosion exceeds maximum repair damage limits, replace the M/R blade with an airworthy M/R blade. (iv) If there is an edge void in the grip pad or in a grip plate or doubler, determine the length and depth using a feeler gauge. Repair the M/R blade if the edge void is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade. (v) If there is an edge void in a grip plate or doubler near the outboard tip, tap inspect the affected area to determine the size and shape of the void. Repair the M/R blade if the edge void is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade. (vi) If there is any loose or damaged adhesive squeeze-out along any of the bond lines, trim or scrape away the adhesive without damaging the adjacent surfaces or parent material of the M/R blade. Determine if there is an edge void or any corrosion by lightly sanding the trimmed area smooth using 280 or finer grit paper. If there is no edge void or corrosion, refinish the sanded area. (vii) If there is an edge delamination along any of the bond lines or a crack in the paint finish, determine if there is an edge void or a crack in the grip pad, grip plate, doubler, or skin by removing paint from the affected area by lightly sanding in a span- wise direction using 180-220 grit paper. If there are no edge voids and no cracks, refinish the sanded area. [[Page 74287]] (viii) If any parent material is removed during any sanding or trimming in paragraphs (f)(2)(vi) or (f)(2)(vii) of this AD, repair the M/R blade if the damage is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade. (g) Special Flight Permits Special flight permits are prohibited. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Fort Worth Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5140; 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. (i) Additional Information Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013, and ASB No. 204-75-1 and ASB No. 205-75-5, both Revision C and both dated April 25, 1979, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may review the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (j) Subject Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blades. Issued in Fort Worth, Texas, on October 18, 2016. James A. Grigg, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-25742 Filed 10-25-16; 8:45 am] BILLING CODE 4910-13-P
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flight tests in combination with http://www.bellcustomer.com/files/. Comments
simulation are used as a part of a You may view this referenced service We gave the public the opportunity to
showing of compliance for information at the FAA, Office of the participate in developing this AD, but
‘‘catastrophic’’ failure conditions. Flight Regional Counsel, Southwest Region, we received no comments on the NPRM
tests are performed only in 10101 Hillwood Pkwy, Room 6N–321, (81 FR 27055, May 5, 2016).
circumstances that use operational Fort Worth, TX 76177.
variations, or extrapolations from other FAA’s Determination
flight performance aspects to address Examining the AD Docket
We have reviewed the relevant
flight safety. You may examine the AD docket on information and determined that an
These special conditions require that the Internet at http:// unsafe condition exists and is likely to
the HeliSAS AP/SAS system installed www.regulations.gov in Docket No. exist or develop on other helicopters of
on an Airbus Helicopters Model EC120B FAA–2015–3821; or in person at the these same type designs and that air
helicopter meet these requirements to Docket Management Facility between 9 safety and the public interest require
adequately address the failure effects adopting the AD requirements as
a.m. and 5 p.m., Monday through
identified by the FHA, and subsequently proposed.
Friday, except Federal holidays. The AD
verified by the SSA, within the defined
docket contains this AD, the economic Related Service Information
design system integrity requirements.
evaluation, any comments received, and Bell issued Alert Service Bulletin
Issued in Fort Worth, Texas, on October 17, other information. The address for the
2016. (ASB) No. UH–1H–13–09, dated January
Docket Office (phone: 800–647–5527) is 14, 2013, for the Model UH–1H
Scott A. Horn, Document Management Facility, U.S. helicopter (ASB UH–1H–13–09). ASB
Assistant Manager, Rotorcraft Directorate, Department of Transportation, Docket UH–1H–13–09 specifies a one-time
Aircraft Certification Service. Operations, M–30, West Building visual inspection, within 10 hours time-
[FR Doc. 2016–25786 Filed 10–25–16; 8:45 am] Ground Floor, Room W12–140, 1200 in-service (TIS), of the lower grip pad
BILLING CODE 4910–13–P New Jersey Avenue SE., Washington, and upper and lower grip plates for
DC 20590. cracks, edge voids, and loose or
FOR FURTHER INFORMATION CONTACT: damaged adhesive squeeze-out. ASB
DEPARTMENT OF TRANSPORTATION UH–1H–13–09 also specifies a repetitive
Charles Harrison, Project Manager, Fort
Federal Aviation Administration Worth Aircraft Certification Office, visual inspection, daily and at every 150
FAA, 10101 Hillwood Pkwy., Fort hours TIS of the lower grip pad, upper
14 CFR Part 39 Worth, TX 76177; telephone (817) 222– and lower grip plates, and all upper and
5140; email charles.c.harrison@faa.gov. the lower doublers for cracks, corrosion,
[Docket No. FAA–2015–3821; Directorate edge voids, and loose or damaged
Identifier 2014–SW–025–AD; Amendment SUPPLEMENTARY INFORMATION: adhesive squeeze-out. Similar
39–18696; AD 2016–22–07] inspections are contained in Bell ASB
Discussion
RIN 2120–AA64 No. 204–75–1 (ASB 204–75–1) and No.
We issued a notice of proposed 205–75–5 (ASB 205–75–5), both
Airworthiness Directives; Bell rulemaking (NPRM) to amend 14 CFR Revision C and both dated April 25,
Helicopter Textron part 39 to remove AD 75–26–05, 1979, for Bell Model 204B and 205A–1
Amendment 39–2457 (40 FR 57783, helicopters, respectively. ASB 204–75–1
AGENCY: Federal Aviation
December 12, 1975) and add a new AD. and ASB 205–75–5 call for daily
Administration (FAA), DOT.
AD 75–26–05 applied to Bell Model inspections and for inspections, rework,
ACTION: Final rule. and refinishing every 1,000 hours TIS or
204B, 205A–1, and 212 helicopters. AD
SUMMARY: We are superseding 75–26–05 required removing and 12 months, whichever occurs first.
Airworthiness Directive (AD) 75–26–05 visually inspecting each M/R blade and, Differences Between This AD and the
for Bell Helicopter Textron (Bell) Model depending on the inspection’s outcome, Service Information
204B, 205A–1 and 212 helicopters. AD repairing or replacing the M/R blade.
This AD requires all inspections every
75–26–05 required removing and The NPRM published in the Federal 25 hours TIS or 2 weeks, whichever
visually inspecting each main rotor Register on May 5, 2016 (81 FR 27055). occurs first. ASB UH–1H–13–09
(M/R) blade and, depending on the The NPRM was prompted by a report of specifies a one-time inspection within
inspection’s outcome, repairing or an M/R blade with multiple fatigue 10 hours TIS, and then a second
replacing the M/R blades. This new AD cracks around the retention bolt hole. repetitive inspection daily and at every
requires more frequent inspections of The NPRM proposed to require more 150 hours TIS, while ASB 204–75–1 and
certain M/R blades and applies to Model frequent inspections of certain M/R ASB 205–75–5 call for daily visual
205A helicopters. This AD does not blades and proposed to remove the inspections, and inspections, rework,
require that helicopter blades be requirement that helicopter blades be and refinishing every 1,000 hours TIS or
removed to conduct the initial visual removed to conduct the initial visual 12 months, whichever occurs first. This
inspections. We are issuing this AD to inspections. The NPRM also proposed AD contains more detailed inspection
detect a crack and prevent failure of an to include the Model 205A in the requirements and a more specific
M/R blade and subsequent loss of applicability but remove the Model 212 inspection area than the instructions in
helicopter control. because similar inspections are required ASB UH–1H–13–09. The service
DATES: This AD is effective November by AD 2011–23–02 (76 FR 68301, information applies to M/R blade, part
Lhorne on DSK30JT082PROD with RULES
30, 2016. November 4, 2011). Finally, the NPRM number (P/N) 204–011–250, and was
ADDRESSES: For service information included specific part-numbered blades issued for Model 204B and 205A–1
identified in this final rule, contact Bell in the applicability so that the proposed helicopters. This AD also applies to
Helicopter Textron, Inc., P.O. Box 482, AD would no longer be required if a P/N 204–011–200 because this blade is
Fort Worth, TX 76101; telephone (817) new blade is designed that is not subject of the same type and susceptible to the
280–3391; fax (817) 280–6466; or at to the unsafe condition. unsafe condition. This AD also applies
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to certain M/R blades installed on the on a substantial number of small entities plates of each M/R blade for a crack and any
Model 205A helicopters. While none of under the criteria of the Regulatory corrosion.
these models are registered in the U.S., Flexibility Act. (ii) On the upper and lower exposed
surfaces of each M/R blade from blade
they were included because of blade
List of Subjects in 14 CFR Part 39 stations 24.5 to 35 for the chord width,
P/N eligibility. visually inspect each layered doubler and
Air transportation, Aircraft, Aviation blade skin for a crack and any corrosion. Pay
Costs of Compliance safety, Incorporation by reference, particular attention for any cracking in a
We estimate that this AD affects 52 Safety. doubler or skin near or at the same blade
helicopters of U.S. Registry and that Adoption of the Amendment station as the blade retention bolt hole (blade
labor costs average $85 a work-hour. station 28).
Based on these estimates, we expect the Accordingly, under the authority (iii) Visually inspect the exposed areas of
following costs: delegated to me by the Administrator, each bond line at the edges of the lower grip
Cleaning and performing all the FAA amends 14 CFR part 39 as pad, upper and lower grip plates, and each
follows: layered doubler (bond lines) on the upper
inspections of a set of M/R blades (2 per and lower surfaces of each M/R blade for the
helicopter) requires a half work-hour. entire length and chord width for an edge
No parts are needed. At an estimated 24 PART 39—AIRWORTHINESS
DIRECTIVES void, any corrosion, loose or damaged
inspections a year, the cost is $1,032 per adhesive squeeze-out, and an edge
helicopter and $53,664 for the U.S. fleet. ■ 1. The authority citation for part 39 delamination. Pay particular attention to any
Replacing an M/R blade requires 12 continues to read as follows:
crack in the paint finish that follows the
work hours and parts cost $90,656 for a outline of a grip pad, grip plate, or doubler,
total cost of $91,676 per blade. Authority: 49 U.S.C. 106(g), 40113, 44701. and to any loose or damaged adhesive
squeeze-out, as these may be the indication
Authority for This Rulemaking § 39.13 [Amended] of an edge void.
■ 2. The FAA amends § 39.13 by (2) If there is a crack, any corrosion, an
Title 49 of the United States Code
removing Airworthiness Directive (AD) edge void, loose or damaged adhesive
specifies the FAA’s authority to issue squeeze-out, or an edge delamination during
rules on aviation safety. Subtitle I, 75–26–05, Amendment 39–2457 (40 FR
any inspection in paragraph (f)(1) of this AD,
Section 106, describes the authority of 57783, December 12, 1975), and adding before further flight, do the following:
the FAA Administrator. Subtitle VII, the following new AD: (i) If there is a crack in a grip pad or any
Aviation Programs, describes in more 2016–22–07 Bell Helicopter Textron: grip plate or doubler, replace the M/R blade
detail the scope of the Agency’s Amendment 39–18696; Docket No. with an airworthy M/R blade.
authority. FAA–2015–3821; Directorate Identifier (ii) If there is a crack in the M/R blade skin
We are issuing this rulemaking under 2014–SW–025–AD. that is within maximum repair damage
the authority described in Subtitle VII, limits, repair the M/R blade. If the crack
(a) Applicability
exceeds maximum repair damage limits,
Part A, Subpart III, Section 44701, This AD applies to Model 204B, 205A, and replace the M/R blade with an airworthy
‘‘General requirements.’’ Under that 205A–1 helicopters with a main rotor (M/R) M/R blade.
section, Congress charges the FAA with blade, part number (P/N) 204–011–200–001 (iii) If there is any corrosion within
promoting safe flight of civil aircraft in or P/N 204–011–250–(all dash numbers), maximum repair damage limits, repair the
air commerce by prescribing regulations installed, certificated in any category. M/R blade. If the corrosion exceeds
for practices, methods, and procedures (b) Unsafe Condition maximum repair damage limits, replace the
the Administrator finds necessary for M/R blade with an airworthy M/R blade.
This AD defines the unsafe condition as a (iv) If there is an edge void in the grip pad
safety in air commerce. This regulation crack in an M/R blade, which could result in
is within the scope of that authority or in a grip plate or doubler, determine the
failure of an M/R blade and subsequent loss length and depth using a feeler gauge. Repair
because it addresses an unsafe condition of helicopter control. the M/R blade if the edge void is within
that is likely to exist or develop on maximum repair damage limits, or replace
(c) Affected ADs
products identified in this rulemaking the M/R blade with an airworthy M/R blade.
action. This AD supersedes AD 75–26–05,
(v) If there is an edge void in a grip plate
Amendment 39–2457 (40 FR 57783,
or doubler near the outboard tip, tap inspect
Regulatory Findings December 12, 1975).
the affected area to determine the size and
We have determined that this AD will (d) Effective Date shape of the void. Repair the M/R blade if the
not have federalism implications under This AD becomes effective November 30, edge void is within maximum repair damage
Executive Order 13132. This AD will 2016. limits, or replace the M/R blade with an
not have a substantial direct effect on airworthy M/R blade.
(e) Compliance (vi) If there is any loose or damaged
the States, on the relationship between
You are responsible for performing each adhesive squeeze-out along any of the bond
the national government and the States, lines, trim or scrape away the adhesive
action required by this AD within the
or on the distribution of power and without damaging the adjacent surfaces or
specified compliance time unless it has
responsibilities among the various already been accomplished prior to that time. parent material of the M/R blade. Determine
levels of government. if there is an edge void or any corrosion by
For the reasons discussed above, I (f) Required Actions lightly sanding the trimmed area smooth
certify that this AD: (1) Within 25 hours time-in-service (TIS) or using 280 or finer grit paper. If there is no
(1) Is not a ‘‘significant regulatory 2 weeks, whichever occurs first, and edge void or corrosion, refinish the sanded
action’’ under Executive Order 12866, thereafter at intervals not to exceed 25 hours area.
(2) Is not a ‘‘significant rule’’ under TIS or 2 weeks, whichever occurs first, clean (vii) If there is an edge delamination along
DOT Regulatory Policies and Procedures the upper and lower exposed surfaces of each any of the bond lines or a crack in the paint
Lhorne on DSK30JT082PROD with RULES
M/R blade from an area starting at the butt finish, determine if there is an edge void or
(44 FR 11034, February 26, 1979), end of the blade to three inches outboard of a crack in the grip pad, grip plate, doubler,
(3) Will not affect intrastate aviation the doublers. Using a 3X or higher power or skin by removing paint from the affected
in Alaska to the extent that a regulatory magnifying glass and a light, inspect as area by lightly sanding in a span-wise
distinction is required and follows: direction using 180–220 grit paper. If there
(4) Will not have a significant (i) Visually inspect the exposed areas of the are no edge voids and no cracks, refinish the
economic impact, positive or negative, lower grip pad and upper and lower grip sanded area.
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(viii) If any parent material is removed DEPARTMENT OF TRANSPORTATION 11590; telephone: 516–228–7355; fax:
during any sanding or trimming in 516–794–5531.
paragraphs (f)(2)(vi) or (f)(2)(vii) of this AD, Federal Aviation Administration
repair the M/R blade if the damage is within SUPPLEMENTARY INFORMATION:
maximum repair damage limits, or replace 14 CFR Part 39 Discussion
the M/R blade with an airworthy M/R blade.
[Docket No. FAA–2015–8464; Directorate We issued a notice of proposed
(g) Special Flight Permits Identifier 2015–NM–050–AD; Amendment rulemaking (NPRM) to amend 14 CFR
Special flight permits are prohibited. 39–18692; AD 2016–22–03] part 39 by adding an AD that would
(h) Alternative Methods of Compliance apply to all Bombardier, Inc. Model
RIN 2120–AA64 DHC–8–400 series airplanes. The NPRM
(AMOCs)
Airworthiness Directives; Bombardier, published in the Federal Register on
(1) The Manager, Fort Worth Aircraft
Inc. Airplanes January 19, 2016 (81 FR 2785) (‘‘the
Certification Office, FAA, may approve
NPRM’’). The NPRM was prompted by
AMOCs for this AD. Send your proposal to:
Charles Harrison, Project Manager, Fort
AGENCY: Federal Aviation a revision by the manufacturer to the
Worth Aircraft Certification Office, FAA,
Administration (FAA), Department of CMR of the ALI, in the MRM, that
10101 Hillwood Pkwy., Fort Worth, TX Transportation (DOT). introduces a new CMR task that requires
76177; telephone (817) 222–5140; email 7- ACTION: Final rule. repetitive operational checks of the
AVS-ASW-170@faa.gov. propeller overspeed governor. The
(2) For operations conducted under a 14
SUMMARY: We are adopting a new NPRM proposed to require revising the
CFR part 119 operating certificate or under airworthiness directive (AD) for all airplane maintenance or inspection
14 CFR part 91, subpart K, we suggest that Bombardier, Inc. Model DHC–8–400 program, as applicable, to incorporate a
you notify your principal inspector, or series airplanes. This AD was prompted new CMR task. We are issuing this AD
lacking a principal inspector, the manager of by a revision by the manufacturer to the to prevent dormant failure of the
the local flight standards district office or Certification Maintenance Requirements propeller overspeed governor, which
certificate holding district office, before (CMR) of the Airworthiness Limitation may lead to a loss of propeller
operating any aircraft complying with this Items (ALI), in the Maintenance overspeed protection and result in high
AD through an AMOC. Requirement Manual (MRM), that propeller drag in flight.
introduces a new CMR task that requires Transport Canada Civil Aviation
(i) Additional Information repetitive operational checks of the (TCCA), which is the aviation authority
Bell Helicopter Alert Service Bulletin propeller overspeed governor. This AD for Canada, has issued Canadian AD
(ASB) No. UH–1H–13–09, dated January 14, requires revising the airplane CF–2014–43, dated December 18, 2014
2013, and ASB No. 204–75–1 and ASB No. maintenance or inspection program, as (referred to after this as the Mandatory
205–75–5, both Revision C and both dated applicable, to incorporate a new CMR Continuing Airworthiness Information,
April 25, 1979, which are not incorporated task. We are issuing this AD to prevent or ‘‘the MCAI’’), to correct an unsafe
by reference, contain additional information dormant failure of the propeller condition for all Bombardier, Inc. Model
about the subject of this AD. For service overspeed governor, which may lead to DHC–8–400 series airplanes. The MCAI
information identified in this AD, contact a loss of propeller overspeed protection states:
Bell Helicopter Textron, Inc., P.O. Box 482, and result in high propeller drag in
Fort Worth, TX 76101; telephone (817) 280– flight. Bombardier Inc. has revised the
3391; fax (817) 280–6466; or at http:// Maintenance Requirement Manual PSM–1–
www.bellcustomer.com/files/. You may DATES: This AD is effective November 84–7, Airworthiness Limitation Items (ALI),
review the service information at the FAA, 30, 2016. Part 2, Section 1, Certification Maintenance
Office of the Regional Counsel, Southwest Requirements (CMR). This revision
Examining the AD Docket
Region, 10101 Hillwood Pkwy., Room 6N– introduces a new CMR task, task number
321, Fort Worth, TX 76177. You may examine the AD docket on 612000–109, for the Operational Check of the
the Internet at http:// Propeller Overspeed Governor to be
(j) Subject www.regulations.gov by searching for performed every 200 flight hours.
Joint Aircraft Service Component (JASC) and locating Docket No. FAA–2015– This new task was introduced to minimize
8464; or in person at the Docket the probability of dormant failure of the
Code: 6210, Main Rotor Blades.
Management Facility between 9 a.m. propeller overspeed governor, which may
Issued in Fort Worth, Texas, on October 18, lead to a loss of propeller overspeed
2016. and 5 p.m., Monday through Friday,
protection and result in high propeller drag
except Federal holidays. The AD docket in-flight.
James A. Grigg,
contains this AD, the regulatory This [Canadian] AD is issued to mandate
Acting Manager, Rotorcraft Directorate, evaluation, any comments received, and
Aircraft Certification Service. the incorporation of a new CMR task for the
other information. The street address for Propeller Overspeed Governor.
[FR Doc. 2016–25742 Filed 10–25–16; 8:45 am] the Docket Office (telephone: 800–647–
BILLING CODE 4910–13–P 5527) is Docket Management Facility, You may examine the MCAI in the
U.S. Department of Transportation, AD docket on the Internet at http://
Docket Operations, M–30, West www.regulations.gov by searching for
Building Ground Floor, Room W12–140, and locating Docket No. FAA–2015–
1200 New Jersey Avenue SE., 8464.
Washington, DC 20590.
Comments
Lhorne on DSK30JT082PROD with RULES
FOR FURTHER INFORMATION CONTACT:
Morton Lee, Aerospace Engineer, We gave the public the opportunity to
Propulsion and Services Branch, ANE– participate in developing this AD. The
173, FAA, New York Aircraft following presents the comment
Certification Office (ACO), 1600 Stewart received on the NPRM and the FAA’s
Avenue, Suite 410, Westbury, NY response.
VerDate Sep<11>2014 15:02 Oct 25, 2016 Jkt 241001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\26OCR1.SGM 26OCR1](https://thefederalregister.org/doc/81_FR_74492/page/3.svg)
Document Created: 2016-10-26 02:17:25
Document Modified: 2016-10-26 02:17:25
| 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. | |
| Dates | This AD is effective November 30, 2016. | |
| Contact | Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5140; email [email protected] | |
| FR Citation | 81 FR 74285 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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