Airworthiness Directives; Enstrom Helicopter Corporation Model F-28A, F-28C, F-28F, TH-28, 280, 280C, 280F, 280FX, 480, and 480B Helicopters, 49177-49180 [E7-16770]
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Federal Register / Vol. 72, No. 166 / Tuesday, August 28, 2007 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2007–18–02 Airbus: Amendment 39–15182.
Docket No. FAA–2007–28379;
Directorate Identifier 2007–NM–077–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 2, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
series airplanes, all certified models, all
serial numbers, certificated in any category;
except Model A300–600 series airplanes; and
except those modified by Airbus Service
Bulletin A300–24–0103, Revision 01, dated
January 11, 2007.
Subject
(d) Air Transport Association (ATA) of
America Code 24: Electrical Power.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
[T]he FAA has published SFAR 88 (Special
Federal Aviation Regulation 88). In their
letters referenced 04/00/02/07/01–L296,
dated March 4th, 2002 and 04/00/02/07/03–
L024, dated February 3rd, 2003, the JAA
(Joint Aviation Authorities) recommended
the application of a similar regulation to the
National Aviation Authorities (NAA).
Under this regulation, all holders of type
certificates for passenger transport aircraft
with either a passenger capacity of 30 or
more, or a payload capacity of 7,500 pounds
(3402 kg) or more, which have received their
certification since January 1st, 1958, are
required to conduct a design review against
explosion risks.
This Airworthiness Directive (AD), which
renders mandatory the modification of the
fuel pump wiring against short circuit, is a
consequence of this design review.
Note: For A310 and A300–600 aircraft,
refer to [EASA] AD 2006–0284R1. [On March
7, 2007, the FAA issued a corresponding
NPRM for Model A310 and A300–600
airplanes, which was published in the
Federal Register (72 FR 11302, March 13,
2007.)]
pwalker on PROD1PC71 with NOTICES
The unsafe condition is chafing of the fuel
pump cables, which could result in short
circuits leading to fuel pump failure,
intermittent operation, arcing, and possible
fuel tank explosion.
Actions and Compliance
(f) Within 31 months after the effective
date of this AD, unless already done, modify
the inner and outer fuel pumps wiring, route
1P and 2P harnesses in the LH (left-hand)
wing and in the RH (right-hand) wing, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
24–0103, Revision 01, dated January 11,
2007. Actions done before the effective date
VerDate Aug<31>2005
16:51 Aug 27, 2007
Jkt 211001
of this AD in accordance with Airbus Service
Bulletin A300–24–0103, dated March 15,
2006, for airplanes under configuration 1 as
defined in the service bulletin, are acceptable
for compliance with the requirements of this
AD.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Stafford,
Aerospace Engineer, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1622; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2007–0066, dated March 13, 2007,
and Airbus Service Bulletin A300–24–0103,
Revision 01, dated January 11, 2007, for
related information.
Material Incorporated by Reference
(i) You must use Airbus Service Bulletin
A300–24–0103, Revision 01, dated January
11, 2007, to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
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49177
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–16911 Filed 8–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26771; Directorate
Identifier 2005–SW–07–AD; Amendment 39–
15059; AD 2007–11–02]
RIN 2120–AA64
Airworthiness Directives; Enstrom
Helicopter Corporation Model F–28A,
F–28C, F–28F, TH–28, 280, 280C, 280F,
280FX, 480, and 480B Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for
Enstrom Helicopter Corporation
(Enstrom) Model F–28A, F–28C, F–28F,
TH–28, 280, 280C, 280F, 280FX, 480,
and 480B helicopters that requires
determining the installation dates for
each main rotor push-pull control rod
(push-pull rod), inspecting the pushpull rods for corrosion, replacing any
push-pull rod which has corrosion that
is severe enough to cause pitting, or has
visible moisture inside the rod, and
repairing each push-pull rod that has
corrosion but no pitting. This
amendment is prompted by one
reported incident in which the
helicopter pilot encountered severe inflight vibration due to the failure of a
push-pull rod, requiring an emergency
landing. The actions specified by this
AD are intended to detect corrosion and
prevent failure of a push-pull rod, and
subsequent loss of control of the
helicopter.
Effective October 2, 2007.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of October 2,
2007.
ADDRESSES: You may get the service
information identified in this AD from
The Enstrom Helicopter Corporation,
Twin County Airport, P.O. Box 490,
Menominee, Michigan 49858.
DATES:
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49178
Federal Register / Vol. 72, No. 166 / Tuesday, August 28, 2007 / Rules and Regulations
Examining the Docket
A
proposal to amend 14 CFR part 39 to
include an AD for the specified model
helicopters was published in the
Federal Register on January 8, 2007 (72
FR 669). That action proposed to require
reviewing the helicopter maintenance
records and determining the installation
dates for the push-pull rods. If the dates
cannot be determined from the
maintenance records, using the ‘‘Date
MFD’’, which is located on the
helicopter data plate, was proposed to
be used as the installation date for the
push-pull rods. That action also
proposed to require a visual inspection
for corrosion on the exterior and interior
of the three push-pull rods, part number
SUPPLEMENTARY INFORMATION:
You may examine the docket that
contains this AD, any comments, and
other information on the Internet at
https://dms.dot.gov or at the Docket
Operations office, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC.
FOR FURTHER INFORMATION CONTACT:
Shawn Malekpour, Aviation Safety
Engineer, FAA, Chicago Aircraft
Certification Office, 2300 East Devon
Ave., Des Plaines, Illinois 60018,
telephone (847) 294–7837, fax (847)
294–7834.
(P/N) 28–16253-all dash numbers (for
Model F–28A, F–28C, F–28F, 280, 280C,
280F, and 280FX helicopters) or P/N
4140532–all dash numbers (for Model
TH–28, 480, and 480B helicopters),
using the compliance times stated in the
following table. Replacing any pushpull rod that has corrosion that is severe
enough to cause pitting or has moisture
inside the rod, and repairing any pushpull rod that has corrosion but no
pitting, was proposed to be required
before further flight. Repairing a pushpull rod consists of cleaning the pushpull rod, applying a protective coating,
and sealing the push-pull rod before
remarking and reinstalling it on a
helicopter.
Helicopter models
Push-pull rod service life
Compliance times
Model F–28A, F–28C, F–28F, 280, 280C,
280F, and 280FX helicopters.
Push-pull rod that has been installed for 20 or
more years.
Model F–28A, F–28C, F–28F, 280, 280C,
280F, and 280FX helicopters.
Model F–28A, F–28C, F–28F, 280, 280C,
280F, and 280FX helicopters.
Push-pull rod that has been installed for 10 or
more years, but less than 20 years.
Push-pull rod that has been installed for less
than 10 years.
Model TH–28, 480, and 480B helicopters .........
Push-pull rod that has been installed for 10 or
more years.
Push-pull rod that has been installed for less
than 10 years.
Inspect within 10 hours time-in-service (TIS)
or at next annual inspection, whichever occurs first.
Inspect within 50 hours TIS or at the next annual inspection, whichever occurs first.
Inspect before the service life of the push-pull
rod reaches 10 years since initial installation.
Inspect within 50 hours TIS or at the next annual inspection, whichever occurs first.
Inspect before the service life of the push-pull
rod reaches 10 years since initial installation.
pwalker on PROD1PC71 with NOTICES
Model TH–28, 480, and 480B helicopters .........
We have reviewed the following
service information:
• Enstrom Helicopter Corporation
Service Directive Bulletin No. 0096,
dated September 10, 2003, which
describes visually inspecting the pushpull rods for corrosion and internal
moisture, provides for repairing light
corrosion, and is applicable to Model F–
28A, F–28C, F–28F, 280, 280C, 280F,
and 280FX helicopters.
• Enstrom Helicopter Corporation
Service Directive Bulletin No. T–019,
dated September 10, 2003, which
describes visually inspecting the pushpull rods for corrosion and internal
moisture, provides for repairing light
corrosion, and is applicable to Model
TH–28, 480, and 480B helicopters.
• Enstrom Helicopter Corporation
Service Information Letter (SIL) No. T–
019, dated December 9, 2003, applicable
to Model TH–28, 480, and 480B
helicopters, which describes visually
inspecting each push-pull rod for a
crack, nick, scratch, dent, corrosion,
damaged threads, bending, and contact
wear. We are not proposing to require
the inspections specified in the SIL.
• Enstrom Helicopter Corporation
Service Information Letter No. 0156,
dated December 9, 2003, applicable to
Model F–28A, F–28C, F–28F, 280, 280C,
280F, and 280FX helicopters, which
VerDate Aug<31>2005
16:51 Aug 27, 2007
Jkt 211001
describes visually inspecting each pushpull rod for a crack, nick, scratch, dent,
corrosion, damaged threads, bending,
and contact wear. We are not proposing
to require the inspections specified in
the SIL.
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. No
comments were received on the
proposal or the FAA’s determination of
the cost to the public. The FAA has
determined that air safety and the
public interest require the adoption of
the rule as proposed.
The FAA estimates that this AD will
affect 378 helicopters of U.S. registry,
and the required actions will take the
following numbers of work hours to
accomplish on each helicopter at an
average labor rate of $80 per work hour:
• 8 work hours to remove,
disassemble, and inspect the 3 pushpull rods;
• 9 work hours to repair corrosion
without pitting, remark each push-pull
rod, and reassemble each push-pull rod;
and
• 3 work hours to reinstall 3 pushpull rods on the helicopter.
Required parts will cost approximately
$900 per helicopter. Based on these
figures, the total cost impact of the AD
on U.S. operators will be $945,000
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Frm 00052
Fmt 4700
Sfmt 4700
($2,500 per helicopter), assuming 3
push-pull rods are replaced on each
helicopter.
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 the 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); and
3. 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. See the DMS to examine the
economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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Federal Register / Vol. 72, No. 166 / Tuesday, August 28, 2007 / Rules and Regulations
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration amends part 39 of the
Federal Aviation Regulations (14 CFR
part 39) as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
2007–11–02 Enstrom Helicopter Company:
Amendment 39–15059. Docket No.
FAA–2006–26771; Directorate Identifier
2005–SW–07–AD.
Applicability: Model F–28A, F–28C, and
F–28F helicopters, excluding serial number
(S/N) 816 and subsequent; Model 280, 280C,
280F, and 280FX helicopters, excluding S/N
2100 and subsequent; and Model TH–28,
480, and 480B helicopters, excluding S/N
5058 and subsequent, certificated in any
category.
Compliance: Required as indicated, unless
accomplished previously.
49179
To detect corrosion and prevent failure of
a main rotor push-pull control rod (push-pull
rod), and subsequent loss of control of the
helicopter, accomplish the following:
(a) Within 10 hours time-in-service (TIS) or
at the next annual inspection, whichever
occurs first, review the helicopter
maintenance records and determine the date
that each push-pull rod, part number (P/N)
28–16253—all dash numbers (for Model F–
28A, F–28C, F–28F, 280, 280C, 280F, and
280FX helicopters) and P/N 4140532—all
dash numbers (for Model TH–28, 480, and
480B helicopters), was installed. If the date
cannot be determined from the maintenance
records, use the ‘‘Date MFD’’, which is
located on the helicopter data plate, as the
installation date for the push-pull rod.
(b) For Model F–28A, F–28C, F–28F, 280,
280C, 280F, and 280FX helicopters, using the
compliance times stated in Table 1 of this
AD, visually inspect the exterior and interior
of each of the three push-pull rods for
corrosion severe enough to cause pitting or
any moisture, paying special attention to the
area of the lower fitting, in accordance with
section 5.1., INSPECTION, in Enstrom
Helicopter Corporation Service Directive
Bulletin No. 0096, dated September 10, 2003
(SDB 0096).
TABLE 1
Helicopter models
Push-pull rod service life
Compliance times
Model F–28A, F–28C, F–28F, 280, 280C,
280F, and 280FX helicopters.
Push-pull rod that has been installed for 20 or
more years.
Model F–28A, F–28C, F–28F, 280, 280C,
280F, and 280FX helicopters.
Model F–28A, F–28C, F–28F, 280, 280C,
280F, and 280FX helicopters.
Push-pull rod that has been installed for 10 or
more years, but less than 20 years.
Push-pull rod that has been installed for less
than 10 years.
Inspect within 10 hours time-in-service (TIS)
or at next annual inspection, whichever occurs first.
Inspect within 50 hours TIS or at the next annual inspection, whichever occurs first.
Inspect before the service life of the push-pull
rod reaches 10 years since initial installation.
(1) Before further flight, if corrosion
without pitting is found on a push-pull rod,
then repair, reassemble, remark, and reinstall
it in accordance with section 5.2., REPAIR/
REASSEMBLY, in SDB 0096.
(2) Before further flight, if corrosion is
found that is severe enough to cause pitting,
or if any moisture is visible on the inside of
a push-pull rod, replace it with an airworthy
push-pull rod.
Note 1: Determining continued
serviceability of the push-pull rods by
inspecting the exterior only of each push-pull
rod is described in Enstrom Helicopter
Corporation Service Information Letter No.
0156, dated December 9, 2003.
(c) For Model TH–28, 480 and 480B
helicopters, using the compliance times
stated in Table 2 of this AD, visually inspect
the exterior and interior of each of the three
push-pull rods for corrosion severe enough to
cause pitting or any moisture, paying special
attention to the area of the lower fitting, in
accordance with section 5.1., INSPECTION,
in Enstrom Helicopter Corporation Service
Directive Bulletin No. T–019, dated
September 10, 2003 (SDB T–019).
TABLE 2
Helicopter models
Push-pull rod service life
Compliance times
Model TH–28, 480, and 480B helicopters .........
Push-pull rod that has been installed for 10 or
more years.
Push-pull rod that has been installed for less
than 10 years.
Inspect within 50 hours TIS or at the next annual inspection, whichever occurs first.
Inspect before the service life of the push-pull
rod reaches 10 years since initial installation.
pwalker on PROD1PC71 with NOTICES
Model TH–28, 480, and 480B helicopters .........
(1) Before further flight, if corrosion
without pitting is found on a push-pull rod,
then repair, reassemble, remark, and reinstall
it in accordance with section 5.2., REPAIR/
REASSEMBLY, in SDB T–019.
VerDate Aug<31>2005
16:51 Aug 27, 2007
Jkt 211001
(2) Before further flight, if corrosion is
found that is severe enough to cause pitting,
or if any moisture is visible on the inside of
a push-pull rod, replace it with an airworthy
push-pull rod.
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Note 2: Determining continued
serviceability of the push-pull rods by
inspecting the exterior only of each push-pull
rod is described in Enstrom Helicopter
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28AUR1
49180
Federal Register / Vol. 72, No. 166 / Tuesday, August 28, 2007 / Rules and Regulations
Corporation Service Information Letter No.
T–019, dated December 9, 2003.
(d) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Chicago Aircraft
Certification Office, Small Airplane
Directorate, FAA, for information about
previously approved alternative methods of
compliance.
(e) The inspection and replacement, if
necessary, shall be done in accordance with
Enstrom Helicopter Corporation Service
Directive Bulletin No. 0096, dated September
10, 2003; Enstrom Helicopter Corporation
Service Directive Bulletin No. T–019, dated
September 10, 2003; Enstrom Helicopter
Corporation Service Information Letter No.
T–019, dated December 9, 2003; or Enstrom
Helicopter Corporation Service Information
Letter No. 0156, dated December 9, 2003, as
applicable. The Director of the Federal
Register approved these incorporations by
reference in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be obtained
from The Enstrom Helicopter Corporation,
Twin County Airport, P.O. Box 490,
Menominee, Michigan 49858. Copies may be
inspected at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(f) This amendment becomes effective on
October 2, 2007.
Issued in Fort Worth, Texas, on July 5,
2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. E7–16770 Filed 8–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003–NM–194–AD; Amendment
39–15177; AD 2007–17–19]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–90–30 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
pwalker on PROD1PC71 with NOTICES
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD),
applicable to certain McDonnell
Douglas Model MD–90–30 airplanes,
that requires repetitive inspections and
functional tests of the static port heater
VerDate Aug<31>2005
16:51 Aug 27, 2007
Jkt 211001
assemblies, and corrective actions if
necessary. The actions specified by this
AD are intended to prevent an electrical
short of the static port heater from
sparking and igniting the insulation
blanket adjacent to the static port heater,
which could result in smoke and/or fire
in the cabin area. This action is
intended to address the identified
unsafe condition.
DATES: Effective October 2, 2007.
The incorporation by reference of a
certain publication listed in the
regulations is approved by the Director
of the Federal Register as of October 2,
2007.
ADDRESSES: The service information
referenced in this AD may be obtained
from Boeing Commercial Airplanes,
Long Beach Division, 3855 Lakewood
Boulevard, Long Beach, California
90846, Attention: Data and Service
Management, Dept. C1–L5A (D800–
0024). This information may be
examined at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, Washington; or at the
FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California.
FOR FURTHER INFORMATION CONTACT:
Natalie Phan-Tran, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount
Boulevard, Lakewood, California
90712–4137; telephone (562) 627–5343;
fax (562) 627–5210.
SUPPLEMENTARY INFORMATION: A
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an airworthiness directive (AD)
that is applicable to certain McDonnell
Douglas Model MD–90–30 airplanes
was published as a supplemental notice
of proposed rulemaking (NPRM) in the
Federal Register on December 20, 2005
(70 FR 75435). That action proposed to
require repetitive inspections and
functional tests of the static port heater
assemblies, repetitive inspections of the
static port heaters and insulators, and
corrective actions if necessary.
Actions Since Issuance of Supplemental
NPRM
We proposed in paragraph (b)(2) of
the supplemental NPRM to require
repetitive inspections for proper
installation of the static port heaters and
insulation. This proposal was in
response to a National Transportation
Safety Board (NTSB) comment on the
original NPRM. However, we have reassessed the safety implications of the
issue based on additional information
that we received from Boeing. Although
we understand the NTSB’s concern, we
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Sfmt 4700
have determined that the inspections in
paragraph (b)(2) of the supplemental
NPRM are not necessary to address the
identified unsafe condition. We have
revised paragraph (b) of this AD to
remove the requirement to inspect for
proper installation for the following
reasons.
We have concluded that the incorrect
stacking of the heater assembly does not
contribute to the heater connector wire
damage and is therefore not a safety
concern.
We based our original decision to
incorporate a one-time inspection for
incorrect stacking into the original
NPRM on the following statement made
to the FAA in Boeing Letter C1–L4L–
03–0700, dated June 3, 2003.
Boeing’s evaluation included Delta’s
recommendation to redesign the ‘‘* * *
heater resistance wires * * *’’ or heater
element to incorporate larger bend radii. The
problems of excessive localized heating near
the bend radii of the element encountered by
Delta may be attributed to heaters that were
assembled improperly due to the AMM error.
Delta’s statements in its report indicate
finding heater blankets improperly
assembled. Boeing concurs with Delta that
this assembly error would cause excessive
heating and Boeing also believes this
condition could lead to delamination or other
damage in the bend radii areas.
Then, in the supplemental NPRM, we
agreed with the NTSB recommendation
to require repetitive inspections to
address any incorrect stacking that
might occur in the future.
After Boeing commented on the
supplemental NPRM (see ‘‘Comments’’
section below), we contacted Boeing to
clarify its comments. At the same time,
in order to better understand the need
for a repetitive inspection for proper
installation as the NTSB recommended,
we asked Boeing to provide us with
additional information on the cause and
effect of improper installation (incorrect
stacking).
We specifically requested that Boeing
clarify the definition of ‘‘excessive
heating’’ and ‘‘other damage in the bend
radii areas.’’ Boeing confirmed that the
bend radii area of the heater assembly
is the internal heating element bend
radii, within the laminated elastomer
and is not the bend radii of the
connector wire. Based on this statement,
we concluded that the incorrect stacking
of the heater as we understood before
does not contribute to heater connector
wire damage.
Our evaluation of the additional
information has resulted in a better
understanding of ‘‘excessive heating.’’
We determined that improper stack-up
of the static port heater might cause the
heater assembly to run longer at the
E:\FR\FM\28AUR1.SGM
28AUR1
]]>Agencies
[Federal Register Volume 72, Number 166 (Tuesday, August 28, 2007)]
[Rules and Regulations]
[Pages 49177-49180]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-16770]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26771; Directorate Identifier 2005-SW-07-AD;
Amendment 39-15059; AD 2007-11-02]
RIN 2120-AA64
Airworthiness Directives; Enstrom Helicopter Corporation Model F-
28A, F-28C, F-28F, TH-28, 280, 280C, 280F, 280FX, 480, and 480B
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
Enstrom Helicopter Corporation (Enstrom) Model F-28A, F-28C, F-28F, TH-
28, 280, 280C, 280F, 280FX, 480, and 480B helicopters that requires
determining the installation dates for each main rotor push-pull
control rod (push-pull rod), inspecting the push-pull rods for
corrosion, replacing any push-pull rod which has corrosion that is
severe enough to cause pitting, or has visible moisture inside the rod,
and repairing each push-pull rod that has corrosion but no pitting.
This amendment is prompted by one reported incident in which the
helicopter pilot encountered severe in-flight vibration due to the
failure of a push-pull rod, requiring an emergency landing. The actions
specified by this AD are intended to detect corrosion and prevent
failure of a push-pull rod, and subsequent loss of control of the
helicopter.
DATES: Effective October 2, 2007.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 2, 2007.
ADDRESSES: You may get the service information identified in this AD
from The Enstrom Helicopter Corporation, Twin County Airport, P.O. Box
490, Menominee, Michigan 49858.
[[Page 49178]]
Examining the Docket
You may examine the docket that contains this AD, any comments, and
other information on the Internet at https://dms.dot.gov or at the
Docket Operations office, West Building Ground Floor, Room W12-140,
1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Shawn Malekpour, Aviation Safety
Engineer, FAA, Chicago Aircraft Certification Office, 2300 East Devon
Ave., Des Plaines, Illinois 60018, telephone (847) 294-7837, fax (847)
294-7834.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for the specified model helicopters was published in the
Federal Register on January 8, 2007 (72 FR 669). That action proposed
to require reviewing the helicopter maintenance records and determining
the installation dates for the push-pull rods. If the dates cannot be
determined from the maintenance records, using the ``Date MFD'', which
is located on the helicopter data plate, was proposed to be used as the
installation date for the push-pull rods. That action also proposed to
require a visual inspection for corrosion on the exterior and interior
of the three push-pull rods, part number (P/N) 28-16253-all dash
numbers (for Model F-28A, F-28C, F-28F, 280, 280C, 280F, and 280FX
helicopters) or P/N 4140532-all dash numbers (for Model TH-28, 480, and
480B helicopters), using the compliance times stated in the following
table. Replacing any push-pull rod that has corrosion that is severe
enough to cause pitting or has moisture inside the rod, and repairing
any push-pull rod that has corrosion but no pitting, was proposed to be
required before further flight. Repairing a push-pull rod consists of
cleaning the push-pull rod, applying a protective coating, and sealing
the push-pull rod before remarking and reinstalling it on a helicopter.
------------------------------------------------------------------------
Push-pull rod
Helicopter models service life Compliance times
------------------------------------------------------------------------
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect within 10
280, 280C, 280F, and 280FX has been installed hours time-in-
helicopters. for 20 or more service (TIS) or at
years. next annual
inspection,
whichever occurs
first.
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect within 50
280, 280C, 280F, and 280FX has been installed hours TIS or at the
helicopters. for 10 or more next annual
years, but less inspection,
than 20 years. whichever occurs
first.
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect before the
280, 280C, 280F, and 280FX has been installed service life of the
helicopters. for less than 10 push-pull rod
years. reaches 10 years
since initial
installation.
Model TH-28, 480, and 480B Push-pull rod that Inspect within 50
helicopters. has been installed hours TIS or at the
for 10 or more next annual
years. inspection,
whichever occurs
first.
Model TH-28, 480, and 480B Push-pull rod that Inspect before the
helicopters. has been installed service life of the
for less than 10 push-pull rod
years. reaches 10 years
since initial
installation.
------------------------------------------------------------------------
We have reviewed the following service information:
Enstrom Helicopter Corporation Service Directive Bulletin
No. 0096, dated September 10, 2003, which describes visually inspecting
the push-pull rods for corrosion and internal moisture, provides for
repairing light corrosion, and is applicable to Model F-28A, F-28C, F-
28F, 280, 280C, 280F, and 280FX helicopters.
Enstrom Helicopter Corporation Service Directive Bulletin
No. T-019, dated September 10, 2003, which describes visually
inspecting the push-pull rods for corrosion and internal moisture,
provides for repairing light corrosion, and is applicable to Model TH-
28, 480, and 480B helicopters.
Enstrom Helicopter Corporation Service Information Letter
(SIL) No. T-019, dated December 9, 2003, applicable to Model TH-28,
480, and 480B helicopters, which describes visually inspecting each
push-pull rod for a crack, nick, scratch, dent, corrosion, damaged
threads, bending, and contact wear. We are not proposing to require the
inspections specified in the SIL.
Enstrom Helicopter Corporation Service Information Letter
No. 0156, dated December 9, 2003, applicable to Model F-28A, F-28C, F-
28F, 280, 280C, 280F, and 280FX helicopters, which describes visually
inspecting each push-pull rod for a crack, nick, scratch, dent,
corrosion, damaged threads, bending, and contact wear. We are not
proposing to require the inspections specified in the SIL.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
The FAA estimates that this AD will affect 378 helicopters of U.S.
registry, and the required actions will take the following numbers of
work hours to accomplish on each helicopter at an average labor rate of
$80 per work hour:
8 work hours to remove, disassemble, and inspect the 3
push-pull rods;
9 work hours to repair corrosion without pitting, remark
each push-pull rod, and reassemble each push-pull rod; and
3 work hours to reinstall 3 push-pull rods on the
helicopter.
Required parts will cost approximately $900 per helicopter. Based on
these figures, the total cost impact of the AD on U.S. operators will
be $945,000 ($2,500 per helicopter), assuming 3 push-pull rods are
replaced on each helicopter.
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 the 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); and
3. 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. See the DMS to examine the economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 49179]]
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2007-11-02 Enstrom Helicopter Company: Amendment 39-15059. Docket
No. FAA-2006-26771; Directorate Identifier 2005-SW-07-AD.
Applicability: Model F-28A, F-28C, and F-28F helicopters,
excluding serial number (S/N) 816 and subsequent; Model 280, 280C,
280F, and 280FX helicopters, excluding S/N 2100 and subsequent; and
Model TH-28, 480, and 480B helicopters, excluding S/N 5058 and
subsequent, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect corrosion and prevent failure of a main rotor push-
pull control rod (push-pull rod), and subsequent loss of control of
the helicopter, accomplish the following:
(a) Within 10 hours time-in-service (TIS) or at the next annual
inspection, whichever occurs first, review the helicopter
maintenance records and determine the date that each push-pull rod,
part number (P/N) 28-16253--all dash numbers (for Model F-28A, F-
28C, F-28F, 280, 280C, 280F, and 280FX helicopters) and P/N
4140532--all dash numbers (for Model TH-28, 480, and 480B
helicopters), was installed. If the date cannot be determined from
the maintenance records, use the ``Date MFD'', which is located on
the helicopter data plate, as the installation date for the push-
pull rod.
(b) For Model F-28A, F-28C, F-28F, 280, 280C, 280F, and 280FX
helicopters, using the compliance times stated in Table 1 of this
AD, visually inspect the exterior and interior of each of the three
push-pull rods for corrosion severe enough to cause pitting or any
moisture, paying special attention to the area of the lower fitting,
in accordance with section 5.1., INSPECTION, in Enstrom Helicopter
Corporation Service Directive Bulletin No. 0096, dated September 10,
2003 (SDB 0096).
Table 1
------------------------------------------------------------------------
Push-pull rod
Helicopter models service life Compliance times
------------------------------------------------------------------------
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect within 10
280, 280C, 280F, and 280FX has been installed hours time-in-
helicopters. for 20 or more service (TIS) or at
years. next annual
inspection,
whichever occurs
first.
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect within 50
280, 280C, 280F, and 280FX has been installed hours TIS or at the
helicopters. for 10 or more next annual
years, but less inspection,
than 20 years. whichever occurs
first.
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect before the
280, 280C, 280F, and 280FX has been installed service life of the
helicopters. for less than 10 push-pull rod
years. reaches 10 years
since initial
installation.
------------------------------------------------------------------------
(1) Before further flight, if corrosion without pitting is found
on a push-pull rod, then repair, reassemble, remark, and reinstall
it in accordance with section 5.2., REPAIR/REASSEMBLY, in SDB 0096.
(2) Before further flight, if corrosion is found that is severe
enough to cause pitting, or if any moisture is visible on the inside
of a push-pull rod, replace it with an airworthy push-pull rod.
Note 1: Determining continued serviceability of the push-pull
rods by inspecting the exterior only of each push-pull rod is
described in Enstrom Helicopter Corporation Service Information
Letter No. 0156, dated December 9, 2003.
(c) For Model TH-28, 480 and 480B helicopters, using the
compliance times stated in Table 2 of this AD, visually inspect the
exterior and interior of each of the three push-pull rods for
corrosion severe enough to cause pitting or any moisture, paying
special attention to the area of the lower fitting, in accordance
with section 5.1., INSPECTION, in Enstrom Helicopter Corporation
Service Directive Bulletin No. T-019, dated September 10, 2003 (SDB
T-019).
Table 2
------------------------------------------------------------------------
Push-pull rod
Helicopter models service life Compliance times
------------------------------------------------------------------------
Model TH-28, 480, and 480B Push-pull rod that Inspect within 50
helicopters. has been installed hours TIS or at the
for 10 or more next annual
years. inspection,
whichever occurs
first.
Model TH-28, 480, and 480B Push-pull rod that Inspect before the
helicopters. has been installed service life of the
for less than 10 push-pull rod
years. reaches 10 years
since initial
installation.
------------------------------------------------------------------------
(1) Before further flight, if corrosion without pitting is found
on a push-pull rod, then repair, reassemble, remark, and reinstall
it in accordance with section 5.2., REPAIR/REASSEMBLY, in SDB T-019.
(2) Before further flight, if corrosion is found that is severe
enough to cause pitting, or if any moisture is visible on the inside
of a push-pull rod, replace it with an airworthy push-pull rod.
Note 2: Determining continued serviceability of the push-pull
rods by inspecting the exterior only of each push-pull rod is
described in Enstrom Helicopter
[[Page 49180]]
Corporation Service Information Letter No. T-019, dated December 9,
2003.
(d) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Chicago Aircraft Certification Office, Small Airplane
Directorate, FAA, for information about previously approved
alternative methods of compliance.
(e) The inspection and replacement, if necessary, shall be done
in accordance with Enstrom Helicopter Corporation Service Directive
Bulletin No. 0096, dated September 10, 2003; Enstrom Helicopter
Corporation Service Directive Bulletin No. T-019, dated September
10, 2003; Enstrom Helicopter Corporation Service Information Letter
No. T-019, dated December 9, 2003; or Enstrom Helicopter Corporation
Service Information Letter No. 0156, dated December 9, 2003, as
applicable. The Director of the Federal Register approved these
incorporations by reference in accordance with 5 U.S.C. 552(a) and 1
CFR part 51. Copies may be obtained from The Enstrom Helicopter
Corporation, Twin County Airport, P.O. Box 490, Menominee, Michigan
49858. Copies may be inspected at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas or at the National Archives and Records Administration (NARA).
For information on the availability of this material at NARA, call
202-741-6030, or go to: https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
(f) This amendment becomes effective on October 2, 2007.
Issued in Fort Worth, Texas, on July 5, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-16770 Filed 8-27-07; 8:45 am]
BILLING CODE 4910-13-P
