Airworthiness Directives; Bombardier Inc. Airplanes, 6688-6692 [2012-3031]
Download as PDF
<![CDATA[
6688
Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules
TABLE 1—HINGE FITTING ASSEMBLY
PART NUMBERS
113T2271–13
113T2271–23
113T2271–29
113T2271–33
113T2271–401
Actions done before the effective date of
this AD in accordance with Part 3 of the
Work Instructions of Boeing Alert Service
Bulletin 767–57A0079, dated June 20, 2002,
are acceptable for compliance with the
requirements of paragraph (h) and (n) of this
AD.
113T2271–14
113T2271–24
113T2271–30
113T2271–34
113T2271–402
(l) Credit for Actions Accomplished in
Accordance With Previous Service
Information
(q) Alternative Methods of Compliance
(AMOCs)
Actions done before July 29, 2003, in
accordance with Boeing Alert Service
Bulletin 767–57A0076, dated October 26,
2000, are acceptable for compliance with the
corresponding requirements of paragraphs
(g), (h), (j), and (k) of this AD.
New Requirements of This AD
(m) Initial Inspection
For Model 767–400ER airplanes identified
in Boeing Alert Service Bulletin 767–
57A0079, Revision 1, dated May 6, 2010, on
which the inspection required in paragraph
(g) of this AD has not been done as of the
effective date of this AD: Before the
accumulation of 6,000 total flight cycles, or
within 750 flight cycles after the effective
date of this AD, whichever occurs later,
perform either a detailed inspection or a
detailed inspection plus an eddy current
inspection to detect cracks or fractures of the
outboard hinge fitting assemblies on the
trailing edge of the inboard main flap, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–57A0079, Revision 1, dated May 6, 2010.
Accomplishment of this inspection
terminates the inspection requirement of
paragraph (g)(2) of this AD.
(n) Repetitive Inspections
mstockstill on DSK4VPTVN1PROD with PROPOSALS
For Model 767–400ER airplanes: Repeat
either inspection specified in paragraph (h)
or (m) of this AD, as applicable, at the time
specified in paragraph (n)(1) or (n)(2) of this
AD, as applicable, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–57A0079, Revision 1,
dated May 6, 2010.
(1) If the most recent inspection was a
detailed inspection, repeat at intervals not to
exceed 300 flight cycles after doing the
detailed inspection.
(2) If the most recent inspections were a
detailed inspection and an eddy current
inspection, repeat at intervals not to exceed
750 flight cycles after doing the detailed
inspection and eddy current inspection.
(o) Optional Terminating Action
For Model 767–400ER airplanes: Replacing
the fittings with new fittings, in accordance
with Part 3 of the Work Instructions of
Boeing Alert Service Bulletin 767–57A0079,
dated June 20, 2002; or Revision 1, dated
May 6, 2010; terminates the repetitive
inspections required by paragraphs (h) and
(n) of this AD.
VerDate Mar<15>2010
16:41 Feb 08, 2012
Jkt 226001
(p) Credit for Actions Accomplished in
Accordance with Previous Service
Information
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0109; Directorate
Identifier 2010–NM–244–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain Bombardier Inc.
Model CL–215–1A10 and CL–215–6B11
(CL–215T Variant) airplanes. The
existing AD currently requires repetitive
inspections to detect cracking of the
lower cap of the wing front and rear
spars at wing station (WS) 51.00, and
the wing lower skin. Additional actions,
if cracking is found, include reworking
the lower cap of the front or rear spar,
inspecting for cracking, and repairing
any cracking. The existing AD also
(r) Related Information
requires reporting inspection results.
Since we issued that AD, we have
(1) For more information about this AD,
received reports of cracking found
contact Berhane Alazar, Aerospace Engineer,
outside the inspection area. This
Airframe Branch, ANM–120S, FAA, Seattle
proposed AD would extend the
Aircraft Certification Office, 1601 Lind
inspection area of the rear spar lower
Avenue SW., Renton, Washington 98057–
cap from WS 51.00 to WS 49.50 and
3356; phone: 425–917–6577; fax: 425–917–
6590; email: berhane.alazar@faa.gov.
modify the ultrasonic inspection
(2) For service information identified in
calibration procedure. We are proposing
this AD, contact Boeing Commercial
this AD to detect and correct cracking of
Airplanes, Attention: Data & Services
the lower caps of the wing front spar
Management, P.O. Box 3707, MC 2H–65,
and rear spar, and lower wing skin,
Seattle, Washington 98124–2207; telephone
which could result in reduced structural
206–544–5000, extension 1; fax 206–766–
integrity of the airplane.
5680; email me.boecom@boeing.com; Internet DATES: We must receive comments on
https://www.myboeingfleet.com. You may
this proposed AD by March 26, 2012.
review copies of the referenced service
ADDRESSES: You may send comments by
information at the FAA, Transport Airplane
any of the following methods:
Directorate, 1601 Lind Avenue SW., Renton,
• Federal eRulemaking Portal: Go to
Washington. For information on the
https://www.regulations.gov. Follow the
availability of this material at the FAA, call
instructions for submitting comments.
425–227–1221.
• Fax: (202) 493–2251.
Issued in Renton, Washington, on January
• Mail: U.S. Department of
27, 2012.
Transportation, Docket Operations,
Kalene C. Yanamura,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Acting Manager, Transport Airplane
Avenue SE., Washington, DC 20590.
Directorate, Aircraft Certification Service.
• Hand Delivery: U.S. Department of
[FR Doc. 2012–2976 Filed 2–8–12; 8:45 am]
Transportation, Docket Operations,
BILLING CODE 4910–13–P
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Bombardier,
ˆ
Inc., 400 Cote-Vertu Road West, Dorval,
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
SUMMARY:
E:\FR\FM\09FEP1.SGM
09FEP1
Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules
´
Quebec H4S 1Y9, Canada; phone: 514–
855–5000; fax: 514–855–7401; email:
thd.crj@aero.bombardier.com; Internet:
https://www.bombardier.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
Since we issued AD 2005–18–05,
Amendment 39–14245 (70 FR 52009,
September 1, 2005) Transport Canada
Civil Aviation (TCCA), which is the
airworthiness authority for Canada, has
issued Airworthiness Directive CF–
1992–26R2, dated September 1, 2010
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Examining the AD Docket
Cracks have been found in the rear spar of
the left wing at Wing Station (WS) 51.00 on
several aircraft in service. On some aircraft,
the cracks propagated through the lower spar
cap and fail-safe straps into the spar web and
the lower wing skin. The cracks are not
visible from outside the aircraft.
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
George Duckett, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Westbury, NY 11590;
telephone (516) 228–7325; fax (516)
794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
mstockstill on DSK4VPTVN1PROD with PROPOSALS
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–0109; Directorate Identifier
2010–NM–244–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On August 24, 2005, we issued AD
2005–18–05, Amendment 39–14245 (70
FR 52009, September 1, 2005). That AD
required actions intended to address an
unsafe condition on Bombardier, Inc.
Model CL–215–1A10, CL–215–6B11
(CL–215T Variant), and CL–215–6B11
(CL–415 Variant) airplanes.
VerDate Mar<15>2010
16:41 Feb 08, 2012
Jkt 226001
*
*
*
*
*
Revision 2 of this [TCCA] AD is issued as
a result of cracks found outside the
inspection area specified in Revision 1. This
revision extends the inspection area of the
rear spar lower cap from WS 51.00 to WS
49.50 and to modify the ultrasonic inspection
calibration procedure.
Cracking of the lower caps of the wing
front spar and rear spar, and lower wing
skin, could result in reduced structural
integrity of the airplane. You may obtain
further information by examining the
MCAI in the AD docket.
AD 2005–18–05, Amendment 39–
14245 (70 FR 52009, September 1,
2005), specifies Model CL–215–6B11
(CL–415 Variant) airplanes in the
applicability, but also specifies serial
numbers 1001 though 1125. The serial
numbers for Model CL–215–6B11 (CL–
415 Variant) airplanes start at 2001. We
have determined that Model CL–215–
6B11 (CL–415 Variant) airplanes are not
subject to the identified unsafe
condition. Therefore, we have removed
Model CL–215–6B11 (CL–415 Variant)
airplanes from the applicability of this
proposed AD.
Relevant Service Information
Bombardier Inc. has issued Alert
Service Bulletin 215–A454, Revision 4,
dated November 18, 2009. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
6689
develop on other products of the same
type design.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 7 products of U.S. registry.
The actions that are required by AD
2005–18–05, Amendment 39–14245 (70
FR 52009, September 1, 2005) and
retained in this proposed AD take about
17 work-hours per product, at an
average labor rate of $85 per work hour.
Based on these figures, the estimated
cost of the currently required actions is
$1,445 per product.
We estimate that it would take about
6 work-hour per product to comply with
the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$3,570, or $510 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 480 work-hours for a cost of
$40,800 per product. We have received
no definitive data that would enable us
to provide a parts cost estimate for the
on-condition requirement specified in
this proposed AD. We have no way of
determining the number of products
that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
E:\FR\FM\09FEP1.SGM
09FEP1
6690
Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules
responsibilities among the various
levels of government.
For the reasons discussed above, 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); and
3. Will not affect intrastate aviation in
Alaska; 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 a
regulatory 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
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14245 (70 FR
52009, September 1, 2005) and adding
the following new AD:
Bombardier, Inc.: Docket No. FAA–2012–
0109; Directorate Identifier 2010–NM–
244–AD.
This AD was prompted by reports of
cracking found outside the inspection area.
We are proposing this AD to detect and
correct cracking of the lower caps of the wing
front spar and rear spar, and lower wing skin,
which could result in reduced structural
integrity of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD
98–04–08, Amendment 39–10321 (63 FR
7640, February 17, 1998), With New Service
Information
(g) Initial Inspection of AD 98–04–08,
Amendment 39–10321 (63 FR 7640,
February 17, 1998), With New Threshold
At the time specified in paragraph (h) of
this AD: Perform an ultrasonic inspection to
detect cracking of the lower cap of the wing
front and rear spars at wing station 51, in
accordance with the Accomplishment
Instructions of Canadair Alert Service
Bulletin 215–A463, Revision 1, dated May
25, 1995, or Bombardier Alert Service
Bulletin 215–A463, Revision 2, dated March
13, 2001 (for the front spar); and Canadair
Alert Service Bulletin 215–A454, Revision 1,
dated May 25, 1995, Bombardier Alert
Service Bulletin 215–A454, Revision 2, dated
January 27, 1999, Bombardier Alert Service
Bulletin 215–A454, Revision 3, dated March
13, 2001, or Bombardier Alert Service
Bulletin 215–A454, Revision 4, dated
November 18, 2009 (for the rear spar). As of
the effective date of this AD, the inspection
must be done in accordance with the
Accomplishment Instructions of Bombardier
Alert Service Bulletin 215–A463, Revision 2,
dated March 13, 2001 (for the front spar); and
Bombardier Alert Service Bulletin 215–A454,
Revision 3, dated March 13, 2001, or
Bombardier Alert Service Bulletin 215–A454,
Revision 4, dated November 18, 2009 (for the
rear spar).
(c) Applicability
This AD applies to the Bombardier Inc.
airplanes; certificated in any category; as
identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model CL–215–1A10 (Water Bomber)
airplanes, serial numbers 1001 through 1125
inclusive.
(2) Model CL–215–6B11 (CL215T Variant)
airplanes, serial numbers 1056 through 1125
inclusive.
(h) Compliance Times
Do the inspections required by paragraph
(g) of this AD at the earlier of the times
specified in paragraphs (h)(1) and (h)(2) of
this AD.
(1) Prior to the accumulation of 3,000 total
flight hours, or within 25 flight hours after
March 4, 1998 (the effective date of AD 98–
04–08, Amendment 39–10321 (63 FR 7640,
February 17, 1998)), whichever occurs later.
(2) At the later of the times specified in
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Prior to the accumulation of 2,500 total
flight hours, or 8,000 total water drops,
whichever occurs first.
(ii) Within 50 flight hours or 150 water
drops after October 6, 2005 (the effective date
of AD 2005–18–05, Amendment 39–14245
(70 FR 52009, September 1, 2005), whichever
occurs first.
(d) Subject
Air Transport Association (ATA) of
America Code 57: Wings.
(i) Repetitive Inspections With New Intervals
Repeat the ultrasonic inspection specified
in paragraph (g) of this AD at the times
(a) Comments Due Date
We must receive comments by March 26,
2012.
(b) Affected ADs
This AD supersedes AD 2005–18–05,
Amendment 39–14245 (70 FR 52009,
September 1, 2005).
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(e) Reason
VerDate Mar<15>2010
16:41 Feb 08, 2012
Jkt 226001
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
specified in paragraph (i)(1) or (i)(2) of this
AD, as applicable.
(1) For airplanes on which any ultrasonic
inspection required by paragraph (a) of AD
98–04–08, Amendment 39–10321 (63 FR
7640, February 17, 1998), has been done
before October 6, 2005: Within 600 flight
hours after the last ultrasonic inspection, do
the ultrasonic inspection specified in
paragraph (g) of this AD. Repeat the
ultrasonic inspection specified in paragraph
(g) of this AD thereafter at intervals not to
exceed 600 flight hours or 2,000 water drops,
whichever occurs first.
(2) For airplanes on which the ultrasonic
inspection required by paragraph (a) of AD
98–04–08, Amendment 39–10321 (63 FR
7640, February 17, 1998), has not been done
before October 6, 2005: After accomplishing
the initial ultrasonic inspection specified in
paragraph (g) of this AD, repeat the ultrasonic
inspection specified in paragraph (g) of this
AD thereafter at intervals not to exceed 600
flight hours or 2,000 water drops, whichever
occurs first.
Restatement of Requirements of AD 2005–
18–05, Amendment 39–14245 (70 FR 52009,
September 1, 2005), With New Service
Information
(j) Ultrasonic Inspection
At the later of the times specified in
paragraphs (j)(1) and (j)(2) of this AD, do an
ultrasonic inspection for cracks of the wing
lower skin, in accordance with the
Accomplishment Instructions of Bombardier
Alert Service Bulletin 215–A454, Revision 3,
dated March 13, 2001; or Bombardier Alert
Service Bulletin 215–A454, Revision 4, dated
November 18, 2009. Thereafter, do the
ultrasonic inspection for cracks of the wing
lower skin at the times specified for the
ultrasonic inspection in paragraph (i) of this
AD.
(1) Within 50 flight hours or 150 water
drops after October 6, 2005, whichever
occurs first.
(2) Before further flight after accomplishing
the first ultrasonic inspection required by
paragraph (g) or (i) of this AD after October
6, 2005.
(k) Cracking Detected
If any cracking is detected during any
inspection required by paragraph (g), (i), or
(j) of this AD, before further flight,
accomplish paragraphs (k)(1) and (k)(2) of
this AD.
(1) Rework the lower cap of the front or
rear spar, as applicable, in accordance with
the Accomplishment Instructions of
Bombardier Alert Service Bulletin 215–A463,
Revision 2, dated March 13, 2001 (for the
front spar); and Bombardier Alert Service
Bulletin 215–A454, Revision 3, dated March
13, 2001; or Bombardier Alert Service
Bulletin 215–A454, Revision 4, dated
November 18, 2009 (for the rear spar).
(2) After doing the rework specified in
paragraph (k)(1) of this AD, do a general
visual inspection, from inside the wing box,
to detect cracks of the front spar web or rear
spar web, as applicable, and the lower skin
area, in accordance with the
Accomplishment Instructions of Bombardier
Alert Service Bulletin 215–A463, Revision 2,
E:\FR\FM\09FEP1.SGM
09FEP1
Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules
dated March 13, 2001 (for the front spar); and
Bombardier Alert Service Bulletin 215–A454,
Revision 3, dated March 13, 2001 (for the rear
spar); or Bombardier Alert Service Bulletin
215–A454, Revision 4, dated November 18,
2009 (for the rear spar). If any cracking is
detected: Before further flight, repair in
accordance with a method approved by the
Manager, New York Aircraft Certification
Office (ACO), FAA; or Transport Canada
Civil Aviation (TCCA) (or its delegated
agent).
(l) Credit for Actions Accomplished in
Accordance With Previous Service
Information
(l) Actions accomplished before October 6,
2005, in accordance with Canadair Alert
Service Bulletin 215–A463, dated April 8,
1993; Canadair Alert Service Bulletin 215–
A463, Revision 1, dated May 25, 1995;
Canadair Alert Service Bulletin 215–A454,
dated October 13, 1993; Canadair Alert
Service Bulletin 215–A454, Revision 1, dated
May 25, 1995; Bombardier Alert Service
Bulletin 215–A454, Revision 2, dated January
27, 1999; are considered acceptable for
compliance with the corresponding actions
specified in this AD.
(2) Actions accomplished before October 6,
2005, in accordance with Bombardier Alert
Wire 215–A454, dated December 23, 1992;
and Bombardier Alert Wire 215–A463, dated
March 26, 1993; are considered acceptable
for compliance with the corresponding
actions specified in this AD.
(m) Reporting Requirement
For any inspection required by AD 2005–
18–05, Amendment 39–14245 (70 FR 52009,
September 1, 2005), that is accomplished
after October 6, 2005, within 30 days after
accomplishing the inspection, submit a
report of any inspection results (both positive
and negative findings) to Bombardier, Inc.,
Canadair, Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec H3C
3G9, Canada; or to Bombardier, Inc., 400
ˆ
´
Cote-Vertu Road West, Dorval, Quebec H4S
1Y9, Canada; telephone 514–855–5000; fax
514–855–7401; email
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com. As of the effective
date of this AD, submit reports to
ˆ
Bombardier, Inc., 400 Cote-Vertu Road West,
´
Dorval, Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401; email
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
New Requirements of This AD
(n) Ultrasonic Inspection of the Rear Spar
Lower Cap
Within the compliance time specified in
paragraph (p) of this AD: Perform an
ultrasonic inspection to detect cracking of the
right and left wing rear spar lower cap
between wing station (WS) 51.00 and WS
49.50, in accordance with paragraph 2.C.,
‘‘Part A,’’ of the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 215–A454, Revision 4, dated
November 18, 2009. Repeat the ultrasonic
inspection thereafter at intervals not to
exceed 600 flight hours or 2,000 water drops,
whichever comes first. Accomplishment of
VerDate Mar<15>2010
16:41 Feb 08, 2012
Jkt 226001
the actions in this paragraph terminates the
inspection requirements of the lower cap of
the wing rear spars at wing station 51.00 of
paragraph (g) of this AD. Accomplishment of
the actions in this paragraph does not
terminate the inspection requirements of the
lower cap of the front wing spars at wing
station 51.00 required by paragraph (g) of this
AD.
(1) If any crack is found in the rear spar
lower cap, before further flight, do a general
visual inspection for cracks from inside the
wing box, of the areas of the rear spar web
and the wing lower skin adjacent to the crack
in the rear spar lower cap, in accordance
with paragraph 2.C., ‘‘Part A,’’ of the
Accomplishment Instructions of Bombardier
Alert Service Bulletin 215–A454, Revision 4,
dated November 18, 2009.
(2) If any cracking is detected during any
ultrasonic or general visual inspection
required by paragraph (n) of this AD, before
further flight, repair in accordance with a
method approved by the Manager, New York
ACO, FAA; or TCCA (or its delegated agent).
(o) Ultrasonic Inspection of the Lower Wing
Skin
Within the compliance time specified in
paragraph (p) of this AD: Perform an
ultrasonic inspection to detect cracking of the
wing lower skin underneath the drag angle
between the front spar and the rear spar at
the left and right WS 51.00, in accordance
with paragraph 2.D., ‘‘Part B,’’ of the
Accomplishment Instructions of Bombardier
Alert Service Bulletin 215–A454, Revision 4,
dated November 18, 2009. Do the ultrasonic
inspection thereafter at intervals not to
exceed 600 flight hours or 2,000 water drops,
whichever comes first. Accomplishment of
the actions in this paragraph terminates the
requirements of paragraph (j) of this AD.
(1) If any crack is found in the wing lower
skin, before further flight, do a general visual
inspection for cracks from inside the wing
box, i.e., the stringers adjacent to the skin
crack in accordance with paragraph 2.D.,
‘‘Part B,’’ of the Accomplishment Instructions
of Bombardier Alert Service Bulletin 215–
A454, Revision 4, dated November 18, 2009.
.
(2) If any cracking is detected during any
ultrasonic or general visual inspection
required by paragraph (o) of this AD, before
further flight, repair in accordance with a
method approved by the Manager, New York
ACO, FAA; or TCCA (or its delegated agent).
(p) Compliance Times for Paragraphs (n)
and (o) of This AD
At the later of the times specified in
paragraphs (p)(1) and (p)(2) of this AD.
(1) Prior to the accumulation of 2,500 total
flight hours, or 8,000 total water drops,
whichever occurs first.
(2) Within 50 flight hours or 150 water
drops after the effective date of this AD,
whichever occurs first.
(q) Credit for Actions Accomplished in
Accordance With Previous Service
Information
Inspections accomplished at WS 51.00
before the effective date of this AD in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
6691
Bulletin 215–A454, Revision 3, dated March
13, 2001, within the last 550 flight hours or
1,850 water drops, are considered acceptable
for compliance with the corresponding action
specified in paragraph (o) of this AD.
(r) Reporting Requirements With New
Address
At the applicable time specified in
paragraph (r)(1) or (r)(2) of this AD, submit
a report of the findings (both positive and
negative) of the inspection required by
paragraphs (n) and (o) of this AD to
Bombardier, Inc., in accordance with
Bombardier Alert Service Bulletin 215–A454,
Revision 4, dated November 18, 2009.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(s) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO,
ANE–170, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; phone: 516–228–7300; fax: 516–794–
5531. Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(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: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
E:\FR\FM\09FEP1.SGM
09FEP1
6692
Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(t) Related Information
Refer to MCAI Airworthiness Directive CF–
1992–26R2, dated September 1, 2010, and the
following service information for related
information.
(1) Bombardier Alert Service Bulletin 215–
A463, Revision 2, dated March 13, 2001.
(2) Bombardier Alert Service Bulletin 215–
A454, Revision 3, dated March 13, 2001.
(3) Bombardier Alert Service Bulletin 215–
A454, Revision 4, dated November 18, 2009.
Issued in Renton, Washington, on January
26, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–3031 Filed 2–8–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0110; Directorate
Identifier 2011–NM–148–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–100,
–200, –200C, –300, –400, and –500
series airplanes equipped with analog
transient suppression devices (ATSDs)
installed in accordance with
Supplemental Type Certificate number
ST00146BO. This proposed AD was
prompted by multiple reports of
corrosion on ATSDs. This proposed AD
would require revising the maintenance
program to incorporate certain
limitations. We are proposing this AD to
detect and correct corrosion on ATSDs,
which could result in the loss of high
voltage transient protection (e.g.,
lightning protection) in the fuel tanks
and consequent fuel tank explosion and
loss of the airplane.
DATES: We must receive comments on
this proposed AD by March 26, 2012.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
16:41 Feb 08, 2012
Jkt 226001
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Goodrich
Corporation, Sensors and Integrated
Systems, 100 Panton Road, Vergennes,
Vermont 05491; phone: 802–877–4580;
fax: 802–877–4444; email:
les.blades@goodrich.com; Internet:
https://www.goodrich.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Marc Ronell, Aerospace Engineer,
Engine and Propeller Directorate, ANE–
150, FAA, New England Aircraft
Certification Office (ACO), 12 New
England Executive Park, Burlington,
Massachusetts 01803; phone: 781–238–
7776; fax: 781–238–7170; email:
marc.ronell@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
2012–0110; Directorate Identifier 2011–
NM–148–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received at least six reports
of corrosion on the housings of ATSDs.
This condition, if not corrected, could
result in the loss of high voltage
transient protection (e.g., lightning
protection) in the fuel tanks and
consequent fuel tank explosion and loss
of the airplane.
Relevant Service Information
We have reviewed Goodrich Principal
Instructions for Continued
Airworthiness Manual for the Analog
Transient Suppression Device
Installation Applicable to Boeing 737–
100 through -500 Airplanes
Supplemental Type Certificate—
ST00146BO, Document T3044–0010–
0101, Revision D, dated September 26,
2011, which describes various
limitations, including Critical Design
Control Limitations (CDCCL),
inspections, and checks of the ATSD,
ground straps, and safe-side harness.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously.
Costs of Compliance
We estimate that this proposed AD
affects 384 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
E:\FR\FM\09FEP1.SGM
09FEP1
]]>Agencies
[Federal Register Volume 77, Number 27 (Thursday, February 9, 2012)]
[Proposed Rules]
[Pages 6688-6692]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-3031]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0109; Directorate Identifier 2010-NM-244-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain Bombardier Inc. Model CL-215-1A10 and CL-
215-6B11 (CL-215T Variant) airplanes. The existing AD currently
requires repetitive inspections to detect cracking of the lower cap of
the wing front and rear spars at wing station (WS) 51.00, and the wing
lower skin. Additional actions, if cracking is found, include reworking
the lower cap of the front or rear spar, inspecting for cracking, and
repairing any cracking. The existing AD also requires reporting
inspection results. Since we issued that AD, we have received reports
of cracking found outside the inspection area. This proposed AD would
extend the inspection area of the rear spar lower cap from WS 51.00 to
WS 49.50 and modify the ultrasonic inspection calibration procedure. We
are proposing this AD to detect and correct cracking of the lower caps
of the wing front spar and rear spar, and lower wing skin, which could
result in reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by March 26, 2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
[[Page 6689]]
Qu[eacute]bec H4S 1Y9, Canada; phone: 514-855-5000; fax: 514-855-7401;
email: thd.crj@aero.bombardier.com; Internet: https://www.bombardier.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: George Duckett, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Westbury, NY 11590;
telephone (516) 228-7325; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0109;
Directorate Identifier 2010-NM-244-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On August 24, 2005, we issued AD 2005-18-05, Amendment 39-14245 (70
FR 52009, September 1, 2005). That AD required actions intended to
address an unsafe condition on Bombardier, Inc. Model CL-215-1A10, CL-
215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes.
Since we issued AD 2005-18-05, Amendment 39-14245 (70 FR 52009,
September 1, 2005) Transport Canada Civil Aviation (TCCA), which is the
airworthiness authority for Canada, has issued Airworthiness Directive
CF-1992-26R2, dated September 1, 2010 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
Cracks have been found in the rear spar of the left wing at Wing
Station (WS) 51.00 on several aircraft in service. On some aircraft,
the cracks propagated through the lower spar cap and fail-safe
straps into the spar web and the lower wing skin. The cracks are not
visible from outside the aircraft.
* * * * *
Revision 2 of this [TCCA] AD is issued as a result of cracks
found outside the inspection area specified in Revision 1. This
revision extends the inspection area of the rear spar lower cap from
WS 51.00 to WS 49.50 and to modify the ultrasonic inspection
calibration procedure.
Cracking of the lower caps of the wing front spar and rear spar, and
lower wing skin, could result in reduced structural integrity of the
airplane. You may obtain further information by examining the MCAI in
the AD docket.
AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005),
specifies Model CL-215-6B11 (CL-415 Variant) airplanes in the
applicability, but also specifies serial numbers 1001 though 1125. The
serial numbers for Model CL-215-6B11 (CL-415 Variant) airplanes start
at 2001. We have determined that Model CL-215-6B11 (CL-415 Variant)
airplanes are not subject to the identified unsafe condition.
Therefore, we have removed Model CL-215-6B11 (CL-415 Variant) airplanes
from the applicability of this proposed AD.
Relevant Service Information
Bombardier Inc. has issued Alert Service Bulletin 215-A454,
Revision 4, dated November 18, 2009. The actions described in this
service information are intended to correct the unsafe condition
identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 7 products of U.S. registry.
The actions that are required by AD 2005-18-05, Amendment 39-14245
(70 FR 52009, September 1, 2005) and retained in this proposed AD take
about 17 work-hours per product, at an average labor rate of $85 per
work hour. Based on these figures, the estimated cost of the currently
required actions is $1,445 per product.
We estimate that it would take about 6 work-hour per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the proposed AD on U.S. operators to be $3,570, or $510 per
product.
In addition, we estimate that any necessary follow-on actions would
take about 480 work-hours for a cost of $40,800 per product. We have
received no definitive data that would enable us to provide a parts
cost estimate for the on-condition requirement specified in this
proposed AD. We have no way of determining the number of products that
may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and
[[Page 6690]]
responsibilities among the various levels of government.
For the reasons discussed above, 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); and
3. Will not affect intrastate aviation in Alaska; 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 a regulatory 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
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]
2. The FAA amends Sec. 39.13 by removing Amendment 39-14245 (70 FR
52009, September 1, 2005) and adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2012-0109; Directorate Identifier
2010-NM-244-AD.
(a) Comments Due Date
We must receive comments by March 26, 2012.
(b) Affected ADs
This AD supersedes AD 2005-18-05, Amendment 39-14245 (70 FR
52009, September 1, 2005).
(c) Applicability
This AD applies to the Bombardier Inc. airplanes; certificated
in any category; as identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model CL-215-1A10 (Water Bomber) airplanes, serial numbers
1001 through 1125 inclusive.
(2) Model CL-215-6B11 (CL215T Variant) airplanes, serial numbers
1056 through 1125 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 57: Wings.
(e) Reason
This AD was prompted by reports of cracking found outside the
inspection area. We are proposing this AD to detect and correct
cracking of the lower caps of the wing front spar and rear spar, and
lower wing skin, which could result in reduced structural integrity
of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
Restatement of Certain Requirements of AD 98-04-08, Amendment 39-10321
(63 FR 7640, February 17, 1998), With New Service Information
(g) Initial Inspection of AD 98-04-08, Amendment 39-10321 (63 FR 7640,
February 17, 1998), With New Threshold
At the time specified in paragraph (h) of this AD: Perform an
ultrasonic inspection to detect cracking of the lower cap of the
wing front and rear spars at wing station 51, in accordance with the
Accomplishment Instructions of Canadair Alert Service Bulletin 215-
A463, Revision 1, dated May 25, 1995, or Bombardier Alert Service
Bulletin 215-A463, Revision 2, dated March 13, 2001 (for the front
spar); and Canadair Alert Service Bulletin 215-A454, Revision 1,
dated May 25, 1995, Bombardier Alert Service Bulletin 215-A454,
Revision 2, dated January 27, 1999, Bombardier Alert Service
Bulletin 215-A454, Revision 3, dated March 13, 2001, or Bombardier
Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009
(for the rear spar). As of the effective date of this AD, the
inspection must be done in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin 215-A463, Revision
2, dated March 13, 2001 (for the front spar); and Bombardier Alert
Service Bulletin 215-A454, Revision 3, dated March 13, 2001, or
Bombardier Alert Service Bulletin 215-A454, Revision 4, dated
November 18, 2009 (for the rear spar).
(h) Compliance Times
Do the inspections required by paragraph (g) of this AD at the
earlier of the times specified in paragraphs (h)(1) and (h)(2) of
this AD.
(1) Prior to the accumulation of 3,000 total flight hours, or
within 25 flight hours after March 4, 1998 (the effective date of AD
98-04-08, Amendment 39-10321 (63 FR 7640, February 17, 1998)),
whichever occurs later.
(2) At the later of the times specified in paragraphs (h)(2)(i)
and (h)(2)(ii) of this AD.
(i) Prior to the accumulation of 2,500 total flight hours, or
8,000 total water drops, whichever occurs first.
(ii) Within 50 flight hours or 150 water drops after October 6,
2005 (the effective date of AD 2005-18-05, Amendment 39-14245 (70 FR
52009, September 1, 2005), whichever occurs first.
(i) Repetitive Inspections With New Intervals
Repeat the ultrasonic inspection specified in paragraph (g) of
this AD at the times specified in paragraph (i)(1) or (i)(2) of this
AD, as applicable.
(1) For airplanes on which any ultrasonic inspection required by
paragraph (a) of AD 98-04-08, Amendment 39-10321 (63 FR 7640,
February 17, 1998), has been done before October 6, 2005: Within 600
flight hours after the last ultrasonic inspection, do the ultrasonic
inspection specified in paragraph (g) of this AD. Repeat the
ultrasonic inspection specified in paragraph (g) of this AD
thereafter at intervals not to exceed 600 flight hours or 2,000
water drops, whichever occurs first.
(2) For airplanes on which the ultrasonic inspection required by
paragraph (a) of AD 98-04-08, Amendment 39-10321 (63 FR 7640,
February 17, 1998), has not been done before October 6, 2005: After
accomplishing the initial ultrasonic inspection specified in
paragraph (g) of this AD, repeat the ultrasonic inspection specified
in paragraph (g) of this AD thereafter at intervals not to exceed
600 flight hours or 2,000 water drops, whichever occurs first.
Restatement of Requirements of AD 2005-18-05, Amendment 39-14245 (70 FR
52009, September 1, 2005), With New Service Information
(j) Ultrasonic Inspection
At the later of the times specified in paragraphs (j)(1) and
(j)(2) of this AD, do an ultrasonic inspection for cracks of the
wing lower skin, in accordance with the Accomplishment Instructions
of Bombardier Alert Service Bulletin 215-A454, Revision 3, dated
March 13, 2001; or Bombardier Alert Service Bulletin 215-A454,
Revision 4, dated November 18, 2009. Thereafter, do the ultrasonic
inspection for cracks of the wing lower skin at the times specified
for the ultrasonic inspection in paragraph (i) of this AD.
(1) Within 50 flight hours or 150 water drops after October 6,
2005, whichever occurs first.
(2) Before further flight after accomplishing the first
ultrasonic inspection required by paragraph (g) or (i) of this AD
after October 6, 2005.
(k) Cracking Detected
If any cracking is detected during any inspection required by
paragraph (g), (i), or (j) of this AD, before further flight,
accomplish paragraphs (k)(1) and (k)(2) of this AD.
(1) Rework the lower cap of the front or rear spar, as
applicable, in accordance with the Accomplishment Instructions of
Bombardier Alert Service Bulletin 215-A463, Revision 2, dated March
13, 2001 (for the front spar); and Bombardier Alert Service Bulletin
215-A454, Revision 3, dated March 13, 2001; or Bombardier Alert
Service Bulletin 215-A454, Revision 4, dated November 18, 2009 (for
the rear spar).
(2) After doing the rework specified in paragraph (k)(1) of this
AD, do a general visual inspection, from inside the wing box, to
detect cracks of the front spar web or rear spar web, as applicable,
and the lower skin area, in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin 215-A463, Revision
2,
[[Page 6691]]
dated March 13, 2001 (for the front spar); and Bombardier Alert
Service Bulletin 215-A454, Revision 3, dated March 13, 2001 (for the
rear spar); or Bombardier Alert Service Bulletin 215-A454, Revision
4, dated November 18, 2009 (for the rear spar). If any cracking is
detected: Before further flight, repair in accordance with a method
approved by the Manager, New York Aircraft Certification Office
(ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its
delegated agent).
(l) Credit for Actions Accomplished in Accordance With Previous Service
Information
(l) Actions accomplished before October 6, 2005, in accordance
with Canadair Alert Service Bulletin 215-A463, dated April 8, 1993;
Canadair Alert Service Bulletin 215-A463, Revision 1, dated May 25,
1995; Canadair Alert Service Bulletin 215-A454, dated October 13,
1993; Canadair Alert Service Bulletin 215-A454, Revision 1, dated
May 25, 1995; Bombardier Alert Service Bulletin 215-A454, Revision
2, dated January 27, 1999; are considered acceptable for compliance
with the corresponding actions specified in this AD.
(2) Actions accomplished before October 6, 2005, in accordance
with Bombardier Alert Wire 215-A454, dated December 23, 1992; and
Bombardier Alert Wire 215-A463, dated March 26, 1993; are considered
acceptable for compliance with the corresponding actions specified
in this AD.
(m) Reporting Requirement
For any inspection required by AD 2005-18-05, Amendment 39-14245
(70 FR 52009, September 1, 2005), that is accomplished after October
6, 2005, within 30 days after accomplishing the inspection, submit a
report of any inspection results (both positive and negative
findings) to Bombardier, Inc., Canadair, Aerospace Group, P.O. Box
6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada; or to
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. As of the effective date of this AD, submit
reports to Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com.
New Requirements of This AD
(n) Ultrasonic Inspection of the Rear Spar Lower Cap
Within the compliance time specified in paragraph (p) of this
AD: Perform an ultrasonic inspection to detect cracking of the right
and left wing rear spar lower cap between wing station (WS) 51.00
and WS 49.50, in accordance with paragraph 2.C., ``Part A,'' of the
Accomplishment Instructions of Bombardier Alert Service Bulletin
215-A454, Revision 4, dated November 18, 2009. Repeat the ultrasonic
inspection thereafter at intervals not to exceed 600 flight hours or
2,000 water drops, whichever comes first. Accomplishment of the
actions in this paragraph terminates the inspection requirements of
the lower cap of the wing rear spars at wing station 51.00 of
paragraph (g) of this AD. Accomplishment of the actions in this
paragraph does not terminate the inspection requirements of the
lower cap of the front wing spars at wing station 51.00 required by
paragraph (g) of this AD.
(1) If any crack is found in the rear spar lower cap, before
further flight, do a general visual inspection for cracks from
inside the wing box, of the areas of the rear spar web and the wing
lower skin adjacent to the crack in the rear spar lower cap, in
accordance with paragraph 2.C., ``Part A,'' of the Accomplishment
Instructions of Bombardier Alert Service Bulletin 215-A454, Revision
4, dated November 18, 2009.
(2) If any cracking is detected during any ultrasonic or general
visual inspection required by paragraph (n) of this AD, before
further flight, repair in accordance with a method approved by the
Manager, New York ACO, FAA; or TCCA (or its delegated agent).
(o) Ultrasonic Inspection of the Lower Wing Skin
Within the compliance time specified in paragraph (p) of this
AD: Perform an ultrasonic inspection to detect cracking of the wing
lower skin underneath the drag angle between the front spar and the
rear spar at the left and right WS 51.00, in accordance with
paragraph 2.D., ``Part B,'' of the Accomplishment Instructions of
Bombardier Alert Service Bulletin 215-A454, Revision 4, dated
November 18, 2009. Do the ultrasonic inspection thereafter at
intervals not to exceed 600 flight hours or 2,000 water drops,
whichever comes first. Accomplishment of the actions in this
paragraph terminates the requirements of paragraph (j) of this AD.
(1) If any crack is found in the wing lower skin, before further
flight, do a general visual inspection for cracks from inside the
wing box, i.e., the stringers adjacent to the skin crack in
accordance with paragraph 2.D., ``Part B,'' of the Accomplishment
Instructions of Bombardier Alert Service Bulletin 215-A454, Revision
4, dated November 18, 2009. .
(2) If any cracking is detected during any ultrasonic or general
visual inspection required by paragraph (o) of this AD, before
further flight, repair in accordance with a method approved by the
Manager, New York ACO, FAA; or TCCA (or its delegated agent).
(p) Compliance Times for Paragraphs (n) and (o) of This AD
At the later of the times specified in paragraphs (p)(1) and
(p)(2) of this AD.
(1) Prior to the accumulation of 2,500 total flight hours, or
8,000 total water drops, whichever occurs first.
(2) Within 50 flight hours or 150 water drops after the
effective date of this AD, whichever occurs first.
(q) Credit for Actions Accomplished in Accordance With Previous Service
Information
Inspections accomplished at WS 51.00 before the effective date
of this AD in accordance with the Accomplishment Instructions of
Bombardier Alert Service Bulletin 215-A454, Revision 3, dated March
13, 2001, within the last 550 flight hours or 1,850 water drops, are
considered acceptable for compliance with the corresponding action
specified in paragraph (o) of this AD.
(r) Reporting Requirements With New Address
At the applicable time specified in paragraph (r)(1) or (r)(2)
of this AD, submit a report of the findings (both positive and
negative) of the inspection required by paragraphs (n) and (o) of
this AD to Bombardier, Inc., in accordance with Bombardier Alert
Service Bulletin 215-A454, Revision 4, dated November 18, 2009.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(s) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York ACO, ANE-170, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the manager of the ACO, send it
to ATTN: Program Manager, Continuing Operational Safety, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590;
phone: 516-228-7300; fax: 516-794-5531. Before using any approved
AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the local flight standards
district office/certificate holding district office. The AMOC
approval letter must specifically reference this AD.
(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: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should
[[Page 6692]]
be directed to the FAA at: 800 Independence Ave. SW., Washington, DC
20591, Attn: Information Collection Clearance Officer, AES-200.
(t) Related Information
Refer to MCAI Airworthiness Directive CF-1992-26R2, dated
September 1, 2010, and the following service information for related
information.
(1) Bombardier Alert Service Bulletin 215-A463, Revision 2,
dated March 13, 2001.
(2) Bombardier Alert Service Bulletin 215-A454, Revision 3,
dated March 13, 2001.
(3) Bombardier Alert Service Bulletin 215-A454, Revision 4,
dated November 18, 2009.
Issued in Renton, Washington, on January 26, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-3031 Filed 2-8-12; 8:45 am]
BILLING CODE 4910-13-P
