Airworthiness Directives; the Cessna Aircraft Company Models 402C and 414A Airplanes, 13362-13365 [05-5382]
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13362
Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
Actions
Compliance
(3) The repetitive inspections required in paragraph (e)(1) of this AD may be terminated if
the wing spar center web repair specified in
paragraph (e)(2) of this AD has been done
on both the left and right wing spar. If one
wing spar center web has been repaired,
then repetitive inspections are still required
on the other one until the repair is done.
Not applicable ..................................................
Not applicable.
May I Request an Alternative Method of
Compliance?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19:
(1) Unless FAA authorizes otherwise, send
your request to your principal inspector. The
principal inspector may add comments and
will send your request to the Manager, Fort
Worth Aircraft Certification Office (ACO),
FAA. For information on any already
approved alternative methods of compliance,
contact Mr. Hung Viet Nguyen, Forth Worth
ACO, FAA, 2601 Meacham Boulevard, Fort
Worth, Texas 76193–0150; telephone: (817)
222–5155; facsimile: (817) 222–5960.
(2) Alternative methods of compliance
approved for AD 99–06–02 are considered
approved as alternative methods of
compliance for this AD.
Series Structural Repair Manual, part number
(P/N) 27–10054–079, pages 57 through 90;
Initial Issue: March 1, 1983; Revision 28,
dated June 24, 1998; and Fairchild SA227
Series Structural Repair Manual, P/N 27–
10054–127, pages 47 through 60; Initial Issue:
December 1, 1991; Revision 7, dated June 24,
1998.
(2) As of May 2, 2005, and in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51, the
Director of the Federal Register approved the
incorporation by reference of Fairchild
Airframe Airworthiness Limitations Manual
ST–UN–M001, SA227 Series, Reissue C
dated January 18, 1991, at the revision levels
stated on page iii and page iv (page iii dated
August 16, 1995, and page iv dated March 8,
2004); Fairchild Airframe Inspection Manual
ST–UN–M002, Reissue A, SA226 Series,
dated December 9, 1986, at the revision
levels stated on page iii and page iv (page iii
dated April 7, 1998, and page iv dated March
8, 2004); and Fairchild Airframe
Airworthiness Limitations Manual ST–UN–
M003, SA227 Commuter Category, Initial
issue dated December 6, 1991, at the revision
levels stated on page iii and page iv (page iii
dated July 29, 2003, and page iv dated March
8, 2004).
(3) You may get a copy from Field Support
Engineering, Fairchild Aircraft, Inc., P.O. Box
790490, San Antonio, Texas 78279–0490.
You may review copies at FAA, Central
Region, Office of the Regional Counsel, 901
Locust, Room 506, Kansas City, Missouri
64106; 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.
DEPARTMENT OF TRANSPORTATION
Does This AD Incorporate Any Material by
Reference?
(g) You must do the inspections required
by this AD following the instructions in
Fairchild Airframe Airworthiness Limitations
Manual ST–UN–M001, Rev. No. C–6, dated
April 7, 1998; Fairchild Airframe
Airworthiness Limitations Manual ST–UN–
M001, Rev. No. C–8, dated March 8, 2004;
Fairchild Airframe Inspection Manual ST–
UN–M002, Rev. No. A–6, dated December 8,
1997; Fairchild Airframe Inspection Manual
ST–UN–M002, Rev. No. A–9, dated March 8,
2004; Fairchild Airframe Airworthiness
Limitations Manual ST–UN–M003, Rev. No.
5, dated April 7, 1998; or Fairchild Airframe
Airworthiness Limitations Manual ST–UN–
M003, Rev. No. 7, dated March 8, 2004, as
applicable. You must do the repairs required
by this AD following the instructions in
Fairchild SA226/227 Series Structural Repair
Manual, part number (P/N) 27–10054–079,
pages 57 through 90; Initial Issue: March 1,
1983; Revision 28, dated June 24, 1998; or
Fairchild SA227 Series Structural Repair
Manual, P/N 27–10054–127, pages 47
through 60; Initial Issue: December 1, 1991;
Revision 7, dated June 24, 1998, as
applicable.
(1) On April 16, 1999 (64 FR 11761, March
10, 1999), and in accordance with 5 U.S.C.
552(a) and 1 CFR part 51, the Director of the
Federal Register approved the incorporation
by reference of Fairchild Airframe
Airworthiness Limitations Manual ST–UN–
M001, Rev. No. C–6, dated April 7, 1998;
Fairchild Airframe Inspection Manual ST–
UN–M002, Rev. No. A–6, dated December 8,
1997; Fairchild Airframe Airworthiness
Limitations Manual ST–UN–M003, Rev. No.
5, dated April 7, 1998; Fairchild SA226/227
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Procedures
Issued in Kansas City, Missouri, on March
14, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–5383 Filed 3–18–05; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20513; Directorate
Identifier 2005–CE–07–AD; Amendment 39–
14022; AD 2005–05–52]
RIN 2120–AA64
Airworthiness Directives; the Cessna
Aircraft Company Models 402C and
414A Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) to
supersede emergency AD 2005–05–51
and AD 2000–23–01 for The Cessna
Aircraft Company (Cessna) Models 402C
and 414A airplanes. This AD contains
the same information as emergency AD
2005–05–52 and publishes the action in
the Federal Register. It requires you to
eddy current inspect the forward wing
spars and visually inspect the aft and
auxiliary spars. This AD is the result of
extensive cracks found on three wing
spars of the affected airplanes. We are
issuing this AD to detect and correct
cracking in the wing spars before the
cracks grow to failure. Such a wing
failure could result in the wing
separating from the airplane with
consequent loss of control of the
airplane.
This AD becomes effective on
March 21, 2005, to all affected persons
who did not receive emergency AD
2005–05–52, issued March 2, 2005.
Emergency AD 2005–05–52 contained
the requirements of this amendment and
became effective immediately upon
receipt. As of March 21, 2005, the
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations.
We must receive any comments on
this AD by April 30, 2005.
ADDRESSES: Use one of the following to
submit comments on this AD:
DATES:
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001.
• Fax: 1–202–493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• To get the service information
identified in this proposed AD, contact
The Cessna Aircraft Company, Product
Support P.O. Box 7706, Wichita, Kansas
67277; telephone: (316) 517–5800;
facsimile: (316) 942–9006.
To view the comments to this AD, go
to https://dms.dot.gov. The docket
number is FAA–2005–20513;
Directorate Identifier 2005–CE–07–AD.
FOR FURTHER INFORMATION CONTACT: Paul
Nguyen, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office,
1801 Airport Road, Mid-Continent
Airport, Wichita, Kansas 67209;
telephone: (316) 946–4125; facsimile:
(316) 946–4107; e-mail:
paul.nguyen@faa.gov.
What
events caused previous FAA AD action?
The FAA has received reports of (and is
analyzing data from) cracks found in the
wings of two Cessna Model 402C
airplanes.
On the first airplane, early
information indicates the airplane had
severe cracking on its left wing in the
vicinity of the forward spar and
outboard engine beam. The main lower
spar cap had completely failed at about
Wing Station (WS) 114. The airplane
also had cracks in the lower wing skin
and the web splice doubler. Also found
were two popped rivets: one between
the heat shield and the wing skin and
another between the factory installed
web splice doublers and web. The
airplane had 20,355 total hours time-inservice (TIS).
During the airplane’s most recent
flights before the cracking was found,
the pilot noticed that roll trim was
required. The flights required the pilot
to use aileron trim for level flight to
keep the wings level. The airplane
landed safely and inspection revealed
the cracks.
On the second airplane, fatigue cracks
were found at about WS 114 in the main
SUPPLEMENTARY INFORMATION:
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Jkt 205001
lower spar cap of another Model 402C
airplane that had over 20,000 total hours
TIS. Fatigue analysis shows that similar
fatigue cracks could also develop in the
wings of the Model 414A airplanes.
Airworthiness Directive (AD) 2000–
23–01, Amendment 39–11971 (65 FR
70645), required repetitive visual
inspections of the forward, aft, and
auxiliary wing spars for cracks on
Cessna Model 402C airplanes. These
inspections are at intervals not to
exceed 110 hours TIS.
Logbook records indicated that both
airplanes with cracked spars were in
compliance with AD 2000–23–01.
The FAA’s analysis of the incidents
presented above showed that, in the
interim, the inspections of AD 2000–23–
01 should be done more frequently and
particular attention paid to certain
areas.
Therefore, FAA issued Emergency AD
2005–05–51 to detect and correct
cracking in the wing spars of the Cessna
Models 402C and 414A airplanes before
the cracks grow to failure. Such a wing
failure could result in the wing
separating from the airplane with
consequent loss of control of the
airplane.
Emergency AD 2005–05–51
superseded AD 2000–23–01 and:
• Required the visual inspections of
the forward, aft, and auxiliary wings
spars for cracks more frequently on
Model 402C airplanes including special
emphasis areas;
• Added inspection requirements for
the Model 414A airplanes; and
• Included provisions to position the
airplane to a home base, hangar,
maintenance facility, etc.
Emergency AD 2005–05–51 did not
affect those airplanes that incorporate a
spar strap modification on each wing
following the original release of (or a
later FAA-approved revision to) Cessna
Service Bulletin MEB02–5 and Cessna
Service Kit SK402–47 (currently at
MEB02–5 Revision 2 and SK402–47B).
What has caused this particular AD
action? Emergency AD 2005–05–51 was
considered an interim action to
immediately require visual inspection of
the forward, aft, and auxiliary wing
spars for cracks. The intent was to
detect immediate and existing cracking
before it grew to wing failure.
The FAA has also received a report of
a third crack found at WS 112 on a
Model 402C airplane.
Cessna has developed new inspection
techniques (eddy current) for the
forward spar that are more effective at
detecting cracks before the structural
integrity of the wing is compromised.
These inspection techniques will allow
for longer intervals between repetitive
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13363
inspections than in emergency AD
2005–05–51.
Recent fatigue analysis that Cessna
did (and the FAA reviewed) reveals that
eddy current inspections of the forward
wing spars combined with visual
inspections of the aft and auxiliary spars
will address the unsafe condition of
these airplanes until long-term
continued operational safety is assured
through the Cessna-developed and FAAapproved spar strap modifications.
Specifically:
• The eddy current inspection will
replace the visual inspection of the
forward spar that emergency AD 2005–
05–51 currently requires; and
• The visual inspections of the aft
and auxiliary spars will be maintained
from emergency AD 2005–05–51, but
will only be required repetitively every
100 hours TIS instead of every 15 hours
TIS.
Cessna has issued the following
service information to include
procedures to eddy current inspect the
Models 402C and 414A airplanes:
• Cessna Service Bulletin MEB99–3,
Revision 2, dated February 28, 2005
(Model 402C); or
• Cessna Service Bulletin MEB00–7,
Revision 2, dated February 28, 2005
(Model 414A).
The FAA’s Determination
After careful review of all available
information related to the subject
presented above, including the abovereferenced service bulletins, FAA has
determined that:
• The forward wings spars should be
inspected using eddy current methods
on Cessna Models 402C and 414A
airplanes;
• The visual inspections of the aft
and auxiliary spars should be
maintained from emergency AD 2005–
05–51 (but not inspected as often); and
• AD action should be taken to detect
and correct cracking in the wing spars
before the cracks grow to failure. Such
a wing failure could result in the wing
separating from the airplane with
consequent loss of control of the
airplane.
Consequently, we issued emergency
AD 2005–05–52 to supersede emergency
AD 2005–05–51.
Why is it important to publish this
AD? The FAA found that immediate
corrective action was required, that
notice and opportunity for prior public
comment were impracticable and
contrary to the public interest, and that
good cause existed to make the AD
effective immediately by individual
letters issued on March 2, 2005, to all
known U.S. operators of Cessna Models
402C and 414A airplanes. These
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
conditions still exist, and the AD is
published in the Federal Register as an
amendment to section 39.13 of the
Federal Aviation Regulations (14 CFR
39.13) to make it effective to all persons.
Comments Invited
Will I have the opportunity to
comment before you issue the rule? This
AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20513; Directorate Identifier
2005–CE–07–AD’’ in the subject line of
your comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the rule that might suggest a need to
modify it. If a person contacts us
through a nonwritten communication,
and that contact relates to a substantive
part of this AD, we will summarize the
contact and place the summary in the
docket. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? 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 AD.
Regulatory Findings
Will this AD impact various entities?
We have determined that this AD will
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15:51 Mar 18, 2005
Jkt 205001
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.
Will this AD involve a significant rule
or regulatory action? For the reasons
discussed above, I certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under 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 a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2005–20513;
Directorate Identifier 2005–CE–07–AD’’
in your request.
Are Any Other ADs Affected by This Action?
(b) This AD supersedes the following:
(1) Emergency AD 2005–05–51, issued
February 20, 2005; and
(2) AD 2000–23–01, Amendment 39–
11971.
What Airplanes Are Affected by This AD?
(c) This AD affects Model 402C and 414A
airplanes, all serial numbers, that:
(1) are certificated in any category; and
(2) do not incorporate a spar strap
modification on each wing spar following the
original release of (or a later FAA-approved
revision to) Cessna Service Bulletin MEB02–
5 and Cessna Service Kit SK402–47
(currently at MEB02–5 Revision 2 and
SK402–47B).
What Is the Unsafe Condition Presented in
This AD?
(d) This AD is the result of extensive cracks
found on three wing spars of the affected
airplanes. We are issuing this AD to detect
and correct cracking in the wing spars before
the cracks grow to failure. Such a wing
failure could result in the wing separating
from the airplane with consequent loss of
control of the airplane.
What Must I Do to Address This Problem?
(e) Visual Inspections for all Model 402C
airplanes With Fewer than 15,000 Hours
List of Subjects in 14 CFR Part 39
Total Time-in-service (TIS): Initially inspect
upon accumulating 10,000 hours TIS on the
Air transportation, Aircraft, Aviation
airplane or at the next inspection that would
safety, Incorporation by reference,
have been required by AD 2000–23–01 or
Safety.
emergency AD 2005–05–51, whichever
occurs later. Repetitively inspect thereafter at
Adoption of the Amendment
intervals not to exceed 110 hours TIS until
accumulating 15,000 hours TIS:
I Accordingly, under the authority
(1) Perform both a visual external and
delegated to me by the Administrator,
internal inspection of the forward, aft, and
the Federal Aviation Administration
auxiliary wing spars for cracks.
amends part 39 of the Federal Aviation
(2) Do these visual inspections following
Regulations (14 CFR part 39) as follows:
the Accomplishment Instructions section of
Cessna Service Bulletin MEB99–3 (Model
PART 39—AIRWORTHINESS
402C), Revision 2, dated February 28, 2005.
DIRECTIVES
(3) When doing the inspections, pay
particular attention to the following areas:
I 1. The authority citation for part 39
(i) Just Outboard of the Engine Beam
continues to read as follows:
(A) The main lower spar cap at Wing
Authority: 49 U.S.C. 106(g), 40113, 44701.
Station (WS) 114.
(B) The three rivets on both the inboard
§ 39.13 [Amended]
and outboard sides of WS 114 (total of six
rivets) in the main lower spar cap as viewed
I 2. The FAA amends § 39.13 by
from the access hole.
removing Airworthiness Directive (AD)
(C) The main spar web at WS 112.5.
2000–23–01, Amendment 39–11971 (65
(ii) Just Inboard of the Inboard Engine
FR 70645), and adding the following new Beam
AD:
(A) The main lower spar cap between WS
2005–05–52 The Cessna Aircraft Company: 80 and WS 89.
(B) The two attach bolts on the main spar
Amendment 39–14022; Docket No.
just inboard of the WS 89.18 rib.
FAA–2005–20513; Directorate Identifier
(f) Eddy Current and Visual Inspections:
2005–CE–07–AD.
Perform eddy current inspections of the
When Does This AD Become Effective?
forward wing spars combined with visual
(a) This AD becomes effective on March 21, inspections of the aft and auxiliary spars. Do
2005, to all affected persons who did not
these inspections following the
receive emergency AD 2005–05–52, issued
Accomplishment Instructions section of
March 2, 2005. Emergency AD 2005–05–52
Cessna Service Bulletin MEB99–3 (Model
contained the requirements of this
402C) or Cessna Service Bulletin MEB00–7
amendment and became effective
(Model 414A), both at Revision 2 and both
immediately upon receipt.
dated February 28, 2005.
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
13365
Affected airplanes
Eddy current and visual inspections
Repetitive Eddy current and visual inspection
interval
(1) For Model 414A airplanes, serial numbers
414A001 through 414A0047 and 414A0049
through 414A0200.
At whichever of the following occurs later:
• Upon accumulating 8,500 hours TIS on the
airplanes;
• At the next inspection that would have been
required by emergency AD 2005–05–51
(required at intervals not to exceed 15
hours TIS); or
• Within the next 2 days after the effective
date of this AD (2 days after receipt for
those who received emergency AD
200505–52).
At whichever of the following occurs later:
• Upon accumulting 15,000 hours TIS on the
airplane;
• At the next inspection that would have been
required by emergency AD 2005–05–51
(required at intervals not to exceed 15
hours TIS); or
• Within the next 2 days after effective date
of this AD (2 days after receipt for those
who received emergency AD 2005–05–52).
Thereafter at intervals not to exceed 100
hours TIS.
May I Request an Alternative Method of
Compliance?
(i) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, Wichita Aircraft Certification Office
(ACO), FAA.
(1) For information on any already
approved alternative methods of compliance
or for further information about this AD,
contact Paul Nguyen, Aerospace Engineer,
FAA, Wichita ACO, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209;
telephone: (316) 946–4125; facsimile: (316)
946–4107; e-mail: paul.nguyen@faa.gov.
(2) Alternative methods of compliance that
were approved for AD 2000–23–01 or
emergency AD 2005–05–51 are not approved
for this emergency AD.
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2005–20513.
(2) For the following airplanes that have 15,000
hours or more TIS or upon accumulating
15,000 hours TIS:
Thereafter at intervals not to exceed 100
hours TIS.
(i) All Model 402C airplanes.
(ii) Model 414A airplanes, serial numbers
414A0201 through 414A1212.
Note: The Cessna service bulletins allow
for either a visual inspection or eddy current
inspection of the forward spars on all
airplanes affected by this AD. Visual
inspections of the forward spars do not
satisfy the requirements of this AD for the
airplanes referenced in paragraphs (f)(1) and
(f)(2) of this AD. These airplanes must have
the forward spars inspected using the eddy
current methods specified in the Cessna
service bulletins.
(g) Cracks Found: If you find any crack on
any forward, aft, or auxiliary wing spar; or in
surrounding structure such as spar webs or
skins during any inspection required by this
AD, before further flight do the following:
(1) Obtain an FAA-approved repair scheme
from the Cessna Aircraft Company, P.O. Box
7706, Wichita, Kansas 67277; telephone:
(316) 517–5800, facsimile: (316) 942–9006;
and
(2) Incorporate this repair scheme.
(h) Reporting Requirement: As soon as
possible, but no later than 24 hours after any
inspection required by this AD and as
defined below:
(1) Submit a report of inspection findings
to the Manager, Wichita Aircraft Certification
Office (ACO), by fax: (316) 946–4107.
(i) Include a report for ‘‘cracks found’’ or
‘‘no cracks found’’ on the initial inspection;
and
(ii) Include a report only for ‘‘cracks
found’’ on the repetitive inspections.
(2) The report must include your name and
a contact phone number, the results of the
findings, a description of any cracking found,
the airplane serial number, and the total
number of hours TIS on the airplane. The
‘‘Lower Wing Spars and Skin Inspection
Report’’ included in Cessna Service Bulletin
MEB99–3 and MEB00–7 may be utilized for
this reporting requirement.
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Does This AD Incorporate Any Material by
Reference?
(j) You must do the actions required by this
AD following the instructions in Cessna
Service Bulletin MEB99–3 (Model 402C) or
Cessna Service Bulletin MEB00–7 (Model
414A), both at Revision 2 and both dated
February 28, 2005. The Director of the
Federal Register approved the incorporation
by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get a copy of this service
information, contact Cessna Aircraft
Company, Product Support P.O. Box 7706,
Wichita, Kansas 67277; telephone: (316) 517–
5800; facsimile: (316) 942–9006. To review
copies of this service information, go to the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
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Issued in Kansas City, Missouri, on March
11, 2005.
Nancy C. Lane,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–5382 Filed 3–18–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99–NE–41–AD; Amendment 39–
14015; AD 2005–06–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80A1/A3
and CF6–80C2A Series Turbofan
Engines, Installed on Airbus Industrie
A300–600 and A310 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
GE CF6–80A1/A3 and CF6–80C2A
series turbofan engines. That AD
currently requires completing one of the
following actions before further flight:
E:\FR\FM\21MRR1.SGM
21MRR1
]]>Agencies
[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13362-13365]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-5382]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20513; Directorate Identifier 2005-CE-07-AD;
Amendment 39-14022; AD 2005-05-52]
RIN 2120-AA64
Airworthiness Directives; the Cessna Aircraft Company Models 402C
and 414A Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) to
supersede emergency AD 2005-05-51 and AD 2000-23-01 for The Cessna
Aircraft Company (Cessna) Models 402C and 414A airplanes. This AD
contains the same information as emergency AD 2005-05-52 and publishes
the action in the Federal Register. It requires you to eddy current
inspect the forward wing spars and visually inspect the aft and
auxiliary spars. This AD is the result of extensive cracks found on
three wing spars of the affected airplanes. We are issuing this AD to
detect and correct cracking in the wing spars before the cracks grow to
failure. Such a wing failure could result in the wing separating from
the airplane with consequent loss of control of the airplane.
DATES: This AD becomes effective on March 21, 2005, to all affected
persons who did not receive emergency AD 2005-05-52, issued March 2,
2005. Emergency AD 2005-05-52 contained the requirements of this
amendment and became effective immediately upon receipt. As of March
21, 2005, the Director of the Federal Register approved the
incorporation by reference of certain publications listed in the
regulations.
We must receive any comments on this AD by April 30, 2005.
ADDRESSES: Use one of the following to submit comments on this AD:
[[Page 13363]]
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-001.
Fax: 1-202-493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
To get the service information identified in this proposed
AD, contact The Cessna Aircraft Company, Product Support P.O. Box 7706,
Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-
9006.
To view the comments to this AD, go to https://dms.dot.gov. The
docket number is FAA-2005-20513; Directorate Identifier 2005-CE-07-AD.
FOR FURTHER INFORMATION CONTACT: Paul Nguyen, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent
Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile:
(316) 946-4107; e-mail: paul.nguyen@faa.gov.
SUPPLEMENTARY INFORMATION: What events caused previous FAA AD action?
The FAA has received reports of (and is analyzing data from) cracks
found in the wings of two Cessna Model 402C airplanes.
On the first airplane, early information indicates the airplane had
severe cracking on its left wing in the vicinity of the forward spar
and outboard engine beam. The main lower spar cap had completely failed
at about Wing Station (WS) 114. The airplane also had cracks in the
lower wing skin and the web splice doubler. Also found were two popped
rivets: one between the heat shield and the wing skin and another
between the factory installed web splice doublers and web. The airplane
had 20,355 total hours time-in-service (TIS).
During the airplane's most recent flights before the cracking was
found, the pilot noticed that roll trim was required. The flights
required the pilot to use aileron trim for level flight to keep the
wings level. The airplane landed safely and inspection revealed the
cracks.
On the second airplane, fatigue cracks were found at about WS 114
in the main lower spar cap of another Model 402C airplane that had over
20,000 total hours TIS. Fatigue analysis shows that similar fatigue
cracks could also develop in the wings of the Model 414A airplanes.
Airworthiness Directive (AD) 2000-23-01, Amendment 39-11971 (65 FR
70645), required repetitive visual inspections of the forward, aft, and
auxiliary wing spars for cracks on Cessna Model 402C airplanes. These
inspections are at intervals not to exceed 110 hours TIS.
Logbook records indicated that both airplanes with cracked spars
were in compliance with AD 2000-23-01.
The FAA's analysis of the incidents presented above showed that, in
the interim, the inspections of AD 2000-23-01 should be done more
frequently and particular attention paid to certain areas.
Therefore, FAA issued Emergency AD 2005-05-51 to detect and correct
cracking in the wing spars of the Cessna Models 402C and 414A airplanes
before the cracks grow to failure. Such a wing failure could result in
the wing separating from the airplane with consequent loss of control
of the airplane.
Emergency AD 2005-05-51 superseded AD 2000-23-01 and:
Required the visual inspections of the forward, aft, and
auxiliary wings spars for cracks more frequently on Model 402C
airplanes including special emphasis areas;
Added inspection requirements for the Model 414A
airplanes; and
Included provisions to position the airplane to a home
base, hangar, maintenance facility, etc.
Emergency AD 2005-05-51 did not affect those airplanes that
incorporate a spar strap modification on each wing following the
original release of (or a later FAA-approved revision to) Cessna
Service Bulletin MEB02-5 and Cessna Service Kit SK402-47 (currently at
MEB02-5 Revision 2 and SK402-47B).
What has caused this particular AD action? Emergency AD 2005-05-51
was considered an interim action to immediately require visual
inspection of the forward, aft, and auxiliary wing spars for cracks.
The intent was to detect immediate and existing cracking before it grew
to wing failure.
The FAA has also received a report of a third crack found at WS 112
on a Model 402C airplane.
Cessna has developed new inspection techniques (eddy current) for
the forward spar that are more effective at detecting cracks before the
structural integrity of the wing is compromised. These inspection
techniques will allow for longer intervals between repetitive
inspections than in emergency AD 2005-05-51.
Recent fatigue analysis that Cessna did (and the FAA reviewed)
reveals that eddy current inspections of the forward wing spars
combined with visual inspections of the aft and auxiliary spars will
address the unsafe condition of these airplanes until long-term
continued operational safety is assured through the Cessna-developed
and FAA-approved spar strap modifications. Specifically:
The eddy current inspection will replace the visual
inspection of the forward spar that emergency AD 2005-05-51 currently
requires; and
The visual inspections of the aft and auxiliary spars will
be maintained from emergency AD 2005-05-51, but will only be required
repetitively every 100 hours TIS instead of every 15 hours TIS.
Cessna has issued the following service information to include
procedures to eddy current inspect the Models 402C and 414A airplanes:
Cessna Service Bulletin MEB99-3, Revision 2, dated
February 28, 2005 (Model 402C); or
Cessna Service Bulletin MEB00-7, Revision 2, dated
February 28, 2005 (Model 414A).
The FAA's Determination
After careful review of all available information related to the
subject presented above, including the above-referenced service
bulletins, FAA has determined that:
The forward wings spars should be inspected using eddy
current methods on Cessna Models 402C and 414A airplanes;
The visual inspections of the aft and auxiliary spars
should be maintained from emergency AD 2005-05-51 (but not inspected as
often); and
AD action should be taken to detect and correct cracking
in the wing spars before the cracks grow to failure. Such a wing
failure could result in the wing separating from the airplane with
consequent loss of control of the airplane.
Consequently, we issued emergency AD 2005-05-52 to supersede
emergency AD 2005-05-51.
Why is it important to publish this AD? The FAA found that
immediate corrective action was required, that notice and opportunity
for prior public comment were impracticable and contrary to the public
interest, and that good cause existed to make the AD effective
immediately by individual letters issued on March 2, 2005, to all known
U.S. operators of Cessna Models 402C and 414A airplanes. These
[[Page 13364]]
conditions still exist, and the AD is published in the Federal Register
as an amendment to section 39.13 of the Federal Aviation Regulations
(14 CFR 39.13) to make it effective to all persons.
Comments Invited
Will I have the opportunity to comment before you issue the rule?
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20513;
Directorate Identifier 2005-CE-07-AD'' in the subject line of your
comments. If you want us to acknowledge receipt of your mailed
comments, send us a self-addressed, stamped postcard with the docket
number written on it; we will date-stamp your postcard and mail it back
to you. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it. If a person contacts us through a
nonwritten communication, and that contact relates to a substantive
part of this AD, we will summarize the contact and place the summary in
the docket. We will consider all comments received by the closing date
and may amend the AD in light of those comments.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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 AD.
Regulatory Findings
Will this AD impact various entities? 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.
Will this AD involve a significant rule or regulatory action? For
the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under 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 a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``Docket No. FAA-2005-20513; Directorate Identifier 2005-CE-07-AD'' in
your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under 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. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2000-23-01, Amendment 39-11971 (65 FR 70645), and adding the following
new AD:
2005-05-52 The Cessna Aircraft Company: Amendment 39-14022; Docket
No. FAA-2005-20513; Directorate Identifier 2005-CE-07-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on March 21, 2005, to all affected
persons who did not receive emergency AD 2005-05-52, issued March 2,
2005. Emergency AD 2005-05-52 contained the requirements of this
amendment and became effective immediately upon receipt.
Are Any Other ADs Affected by This Action?
(b) This AD supersedes the following:
(1) Emergency AD 2005-05-51, issued February 20, 2005; and
(2) AD 2000-23-01, Amendment 39-11971.
What Airplanes Are Affected by This AD?
(c) This AD affects Model 402C and 414A airplanes, all serial
numbers, that:
(1) are certificated in any category; and
(2) do not incorporate a spar strap modification on each wing
spar following the original release of (or a later FAA-approved
revision to) Cessna Service Bulletin MEB02-5 and Cessna Service Kit
SK402-47 (currently at MEB02-5 Revision 2 and SK402-47B).
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of extensive cracks found on three
wing spars of the affected airplanes. We are issuing this AD to
detect and correct cracking in the wing spars before the cracks grow
to failure. Such a wing failure could result in the wing separating
from the airplane with consequent loss of control of the airplane.
What Must I Do to Address This Problem?
(e) Visual Inspections for all Model 402C airplanes With Fewer
than 15,000 Hours Total Time-in-service (TIS): Initially inspect
upon accumulating 10,000 hours TIS on the airplane or at the next
inspection that would have been required by AD 2000-23-01 or
emergency AD 2005-05-51, whichever occurs later. Repetitively
inspect thereafter at intervals not to exceed 110 hours TIS until
accumulating 15,000 hours TIS:
(1) Perform both a visual external and internal inspection of
the forward, aft, and auxiliary wing spars for cracks.
(2) Do these visual inspections following the Accomplishment
Instructions section of Cessna Service Bulletin MEB99-3 (Model
402C), Revision 2, dated February 28, 2005.
(3) When doing the inspections, pay particular attention to the
following areas:
(i) Just Outboard of the Engine Beam
(A) The main lower spar cap at Wing Station (WS) 114.
(B) The three rivets on both the inboard and outboard sides of
WS 114 (total of six rivets) in the main lower spar cap as viewed
from the access hole.
(C) The main spar web at WS 112.5.
(ii) Just Inboard of the Inboard Engine Beam
(A) The main lower spar cap between WS 80 and WS 89.
(B) The two attach bolts on the main spar just inboard of the WS
89.18 rib.
(f) Eddy Current and Visual Inspections: Perform eddy current
inspections of the forward wing spars combined with visual
inspections of the aft and auxiliary spars. Do these inspections
following the Accomplishment Instructions section of Cessna Service
Bulletin MEB99-3 (Model 402C) or Cessna Service Bulletin MEB00-7
(Model 414A), both at Revision 2 and both dated February 28, 2005.
[[Page 13365]]
------------------------------------------------------------------------
Repetitive Eddy
Affected airplanes Eddy current and current and visual
visual inspections inspection interval
------------------------------------------------------------------------
(1) For Model 414A At whichever of the Thereafter at
airplanes, serial numbers following occurs intervals not to
414A001 through 414A0047 later: exceed 100 hours
and 414A0049 through Upon TIS.
414A0200. accumulating 8,500
hours TIS on the
airplanes;.
At the next
inspection that
would have been
required by
emergency AD 2005-
05-51 (required at
intervals not to
exceed 15 hours
TIS); or.
Within the
next 2 days after
the effective date
of this AD (2 days
after receipt for
those who received
emergency AD 200505-
52).
(2) For the following At whichever of the Thereafter at
airplanes that have 15,000 following occurs intervals not to
hours or more TIS or upon later: exceed 100 hours
accumulating 15,000 hours Upon TIS.
TIS: accumulting 15,000
hours TIS on the
airplane;.
At the next
inspection that
would have been
required by
emergency AD 2005-
05-51 (required at
intervals not to
exceed 15 hours
TIS); or.
Within the
next 2 days after
effective date of
this AD (2 days
after receipt for
those who received
emergency AD 2005-
05-52).
(i) All Model 402C
airplanes.
(ii) Model 414A
airplanes, serial
numbers 414A0201
through 414A1212.
------------------------------------------------------------------------
Note: The Cessna service bulletins allow for either a visual
inspection or eddy current inspection of the forward spars on all
airplanes affected by this AD. Visual inspections of the forward
spars do not satisfy the requirements of this AD for the airplanes
referenced in paragraphs (f)(1) and (f)(2) of this AD. These
airplanes must have the forward spars inspected using the eddy
current methods specified in the Cessna service bulletins.
(g) Cracks Found: If you find any crack on any forward, aft, or
auxiliary wing spar; or in surrounding structure such as spar webs
or skins during any inspection required by this AD, before further
flight do the following:
(1) Obtain an FAA-approved repair scheme from the Cessna
Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277; telephone:
(316) 517-5800, facsimile: (316) 942-9006; and
(2) Incorporate this repair scheme.
(h) Reporting Requirement: As soon as possible, but no later
than 24 hours after any inspection required by this AD and as
defined below:
(1) Submit a report of inspection findings to the Manager,
Wichita Aircraft Certification Office (ACO), by fax: (316) 946-4107.
(i) Include a report for ``cracks found'' or ``no cracks found''
on the initial inspection; and
(ii) Include a report only for ``cracks found'' on the
repetitive inspections.
(2) The report must include your name and a contact phone
number, the results of the findings, a description of any cracking
found, the airplane serial number, and the total number of hours TIS
on the airplane. The ``Lower Wing Spars and Skin Inspection Report''
included in Cessna Service Bulletin MEB99-3 and MEB00-7 may be
utilized for this reporting requirement.
May I Request an Alternative Method of Compliance?
(i) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Wichita Aircraft
Certification Office (ACO), FAA.
(1) For information on any already approved alternative methods
of compliance or for further information about this AD, contact Paul
Nguyen, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road,
Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-
4125; facsimile: (316) 946-4107; e-mail: paul.nguyen@faa.gov.
(2) Alternative methods of compliance that were approved for AD
2000-23-01 or emergency AD 2005-05-51 are not approved for this
emergency AD.
Does This AD Incorporate Any Material by Reference?
(j) You must do the actions required by this AD following the
instructions in Cessna Service Bulletin MEB99-3 (Model 402C) or
Cessna Service Bulletin MEB00-7 (Model 414A), both at Revision 2 and
both dated February 28, 2005. The Director of the Federal Register
approved the incorporation by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of
this service information, contact Cessna Aircraft Company, Product
Support P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-
5800; facsimile: (316) 942-9006. To review copies of this service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. To
view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC 20590-001 or on the Internet
at https://dms.dot.gov. The docket number is FAA-2005-20513.
Issued in Kansas City, Missouri, on March 11, 2005.
Nancy C. Lane,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-5382 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P
