Airworthiness Directives; The Boeing Company Airplanes, 16654-16659 [2022-05691]
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Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules
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 adding
the following new airworthiness
directive:
■
Bell Textron Canada Limited (Type
Certificate Previously Held by Bell
Helicopter Textron Canada Limited):
Docket No. FAA–2022–0286; Project
Identifier AD–2021–01081–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by May 9, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Canada
Limited (type certificate previously held by
Bell Helicopter Textron Canada Limited)
Model 206L, 206L–1, 206L–3, and 206L–4
helicopters, certificated in any category, with
main rotor (M/R) blade part number (P/N)
20633000–101 with serial number A007,
A008, A009, or A012 through A104 inclusive
installed under Supplemental Type
Certificate SR02684LA.
(d) Subject
Joint Aircraft System Component (JASC)
Code: 6210, Main Rotor Blades.
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(e) Unsafe Condition
This AD was prompted by reports of
delamination of M/R blades. The FAA is
issuing this AD to address delamination of an
M/R blade initiating in the 90° plies at the
lower inboard end of the weight pocket
receptacle. The unsafe condition, if not
addressed, could result in reduced structural
integrity of the M/R blade, excessive
vibration, and subsequent loss of control of
the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Accomplish the actions required by
paragraph (g)(2) of this AD at the following
compliance time, whichever occurs later:
(i) Before the M/R blade accumulates 400
total hours time-in-service (TIS) or 2,400
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engine starts since initial installation on any
helicopter, whichever occurs first; or
(ii) Within 100 hours TIS after the effective
date of this AD.
(2) Remove each M/R blade from the
helicopter, place it on a flat, stable surface,
and accomplish the following:
(i) Use a permanent marker to draw
rectangular inspection ‘‘Zone 1’’ on the upper
surface of the M/R blade at M/R blade
stations 186.0 and 191.0, beginning 1.1
inches from the leading edge of the M/R
blade to 4.9 inches from the leading edge of
the M/R blade. Draw lines from the inboard
end to the outboard end to connect each end
at 1.1 inches and 4.9 inches. Draw parallel
lines from the inboard end of the inspection
zone to the outboard end of the inspection
zone, with the lines spaced 0.50 inch apart.
Note 1 to paragraph (g)(2)(i): This note
applies to paragraphs (g)(2)(i) and (ii) of this
AD. Figure 4 of Van Horn Aviation, L.L.C.,
Service Bulletin Notice No. 33000–4R3,
dated November 8, 2021 (SB 33000–4R3)
depicts ‘‘Zone 1’’ and ‘‘Zone 2.’’
(ii) Use a permanent marker to draw
rectangular inspection ‘‘Zone 2’’ on the lower
surface of the M/R blade at M/R blade
stations 186.0 and 191.0, beginning from the
forward edge of the weight receptacle pocket
and extending 1 inch in the direction
towards the leading edge of the M/R blade.
Draw lines from the inboard end to the
outboard end to connect each end at the
weight receptacle pocket and 1 inch forward
of the weight receptacle pocket. Draw
parallel lines from the inboard end of the
inspection zone to the outboard end of the
inspection zone, with the lines spaced 0.50
inch apart.
(iii) Using composite tap hammer Abaris
Training Tap Hammer P/N ABATH, HeatCon
Tap Hammer P/N HCS1104–01, Brown Tool
Composite Tap Hammer P/N BAT–CTH8, or
MATCO Tools Composite Tap Hammer P/N
T4BAT–CTH8, tap inspect the areas within
‘‘Zone 1’’ and ‘‘Zone 2’’ for any delamination
by following Tap Inspect Balance Receptacle,
paragraph A.(4) of SB 33000–4R3. Where SB
33000–4R3 specifies to mark the location
where the delamination starts, use a
permanent marker.
(iv) If there are any marks where the
delamination starts, connect the marks
indicating the delamination location and
measure the length at the farthest point from
the inboard end of the inspection area.
(v) If there is any delamination in the lower
surface inspection zone (‘‘Zone 2’’) that is 6.0
or more inches in length or if there is any
delamination in the upper surface inspection
zone (‘‘Zone 1’’), before further flight, remove
the M/R blade from service.
(3) Thereafter repeat the actions required
by paragraph (g)(2) of this AD at intervals not
to exceed 400 hours TIS or 2,400 engine
starts, whichever occurs first.
(4) If there is any delamination, within 30
days after accomplishing the actions required
by paragraphs (g)(1) or (3) of this AD, report
each delamination size and location, and the
total hours TIS and total engine starts since
initial installation of the M/R blade, to Mr.
Dean Rosenlof, Van Horn Aviation, L.L.C.,
1510 West Drake Drive, Tempe, AZ 85283, or
by email to info@vanhornaviation.com.
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(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (i)(1) of
this AD. Information may be emailed to: 9ANM-LAACO-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.
(i) Related Information
(1) For more information about this AD,
contact Peter Jarzomb, Aerospace Engineer,
Airframe Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, FAA,
3960 Paramount Blvd., Lakewood, CA 90712;
telephone (562) 627–5234; email
peter.jarzomb@faa.gov.
(2) For service information identified in
this AD, contact Van Horn Aviation, L.L.C.,
ATTN: Dean Rosenlof, 1510 West Drake
Drive, Tempe, AZ 85283; telephone (480)
483–4202; email dean@vanhornaviation.com.
You may view this service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
Issued on March 15, 2022.
Derek Morgan,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–05874 Filed 3–23–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0148; Project
Identifier AD–2021–00922–T]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2015–12–03, which applies to certain
The Boeing Company Model 777–200,
–200LR, –300, and –300ER series
airplanes. AD 2015–12–03 requires
repetitive freeplay inspections and
lubrication of the right and left
SUMMARY:
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Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules
elevators, rudder, and rudder tab, and
related investigative and corrective
actions if necessary. Since the FAA
issued AD 2015–12–03, engineering
testing revealed that the force being
applied to the elevator to detect
excessive freeplay was insufficient. This
proposed AD would continue to require
certain actions in AD 2015–12–03 for
certain airplanes, and would require
revising the existing maintenance or
inspection program, as applicable, for
certain other airplanes, to incorporate a
revised or new elevator freeplay
maintenance procedure, as applicable.
This proposed AD would also add
airplanes to the applicability. The FAA
is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments
on this proposed AD by May 9, 2022.
ADDRESSES: 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 NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.com. You may view
this service information at the FAA,
Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2022–
0148.
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Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2022–0148; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
NPRM, any comments received, and
other information. The street address for
Docket Operations is listed above.
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16:36 Mar 23, 2022
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Luis
Cortez-Muniz, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax:
(206) 231–3958; email: Luis.A.CortezMuniz@faa.gov.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2022–0148; Project Identifier AD–
2021–00922–T’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend the proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this proposed
AD.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Luis Cortez-Muniz,
Aerospace Engineer, Airframe Section,
FAA, Seattle ACO Branch, 2200 South
216th St., Des Moines, WA 98198;
phone and fax: (206) 231–3958; email:
Luis.A.Cortez-Muniz@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
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Background
The FAA issued AD 2015–12–03,
Amendment 39–18176 (80 FR 34252,
June 16, 2015) (AD 2015–12–03), for
certain The Boeing Company Model
777–200, –200LR, –300, and –300ER
series airplanes. AD 2015–12–03 was
prompted by the manufacturer’s
determination that the procedure for the
rudder freeplay inspection available at
the time did not properly detect
excessive freeplay in the rudder control
load loop. AD 2015–12–03 requires
repetitive freeplay inspections and
lubrication of the right and left
elevators, rudder, and rudder tab, and
related investigative and corrective
actions if necessary. The agency issued
AD 2015–12–03 to detect and correct
excessive wear in the load loop
components of the control surfaces,
which could lead to excessive freeplay
of the control surfaces, flutter, and
consequent loss of control of the
airplane.
AD 2015–12–03 superseded AD 2007–
13–05, Amendment 39–15109 (72 FR
33856, June 20, 2007).
Actions Since AD 2015–12–03 Was
Issued
Since the FAA issued AD 2015–12–
03, engineering testing revealed that the
force being applied to the elevator to
detect excessive freeplay was
insufficient. The original bypass test
setup for the power control unit (PCU),
which used a hydraulic
depressurization method, was found to
be unreliable for putting the adjacent
PCU into bypass mode, and a new
elevator freeplay maintenance
procedure is necessary. Model 777F
airplanes were not added to the
applicability in AD 2015–12–03 because
there was a certification maintenance
requirement (CMR) task to accomplish
the freeplay inspections for those
airplanes; therefore, the FAA has
determined that it is necessary for
operators to revise the maintenance or
inspection program to update the
elevator freeplay procedures for Model
777F airplanes.
FAA’s Determination
The FAA is issuing this NPRM after
determining that the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Special
Attention Service Bulletin 777–27–
0062, Revision 4, dated July 15, 2021.
This service information specifies
procedures for changing the elevator
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Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules
freeplay instructions by adding changes
to the input force, elevator freeplay
limit, and PCU bypass test setup.
This proposed AD would also require
Boeing Special Attention Service
Bulletin 777–27–0062, Revision 2, dated
January 27, 2014, which the Director of
the Federal Register approved for
incorporation by reference as of July 21,
2015 (80 FR 34253, June 16, 2015).
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Proposed AD Requirements in This
NPRM
This proposed AD would retain
certain requirements of AD 2015–12–03
and require accomplishing the actions
specified in accordance with updated
service information, including
corrective actions, such as repairs,
already described for Model 777–200,
–200LR, –300, and –300ER airplanes.
This proposed AD would also add
Model 777F series airplanes to the
applicability. For Model 777F series
airplanes, this proposed AD would
require revising the existing
maintenance or inspection program, as
applicable, to incorporate a new
elevator freeplay maintenance
procedure. For information on the
procedures and compliance times, see
this service information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2022–
0148.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 281
airplanes of U.S. registry. The FAA
estimates the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Required actions
Labor cost
Measurement (inspection),
elevator.
Lubrication, elevator .........
4 work-hours × $85 per hour = $340
per measurement (inspection) cycle.
17 work-hours × $85 per hour = $1,445
per lubrication cycle.
4 work-hours × $85 per hour = $340
per measurement (inspection) cycle.
7 work-hours × $85 per hour = $595
per lubrication cycle.
3 work-hours × $85 per hour = $255
per measurement (inspection) cycle.
5 work-hours × $85 per hour = $425
per lubrication cycle.
Measurement (inspection),
rudder.
Lubrication, rudder ............
Measurement (inspection),
rudder tab.
Lubrication, rudder tab ......
The FAA has received no definitive
data that would enable the agency to
provide cost estimates for the oncondition corrective actions specified in
this proposed AD.
The FAA has determined that revising
the existing maintenance or inspection
program takes an average of 90 workhours per operator, although the agency
recognizes that this number may vary
from operator to operator. Since
operators incorporate maintenance or
inspection program changes for their
affected fleet(s), the FAA has
determined that a per-operator estimate
is more accurate than a per-airplane
estimate. Therefore, the FAA estimates
the average total cost per Model 777F
operator to be $7,650 (90 work-hours ×
$85 per work-hour).
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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.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701, General requirements. Under
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Parts cost
$0
0
0
0
0
0
Cost per product
Cost on U.S. operators
(218)
$340 per measurement
(inspection) cycle.
$1,445 per lubrication
cycle.
$340 per measurement
(inspection) cycle.
$595 per lubrication cycle
$74,120 per measurement
(inspection) cycle.
$315,010 per lubrication
cycle.
$74,230 per measurement
(inspection) cycle.
$129,710 per lubrication
cycle.
$55,590 per measurement
(inspection) cycle.
$92,650 per lubrication
cycle.
$255 per measurement
(inspection) cycle.
$425 per lubrication cycle
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
List of Subjects in 14 CFR Part 39
Regulatory Findings
PART 39—AIRWORTHINESS
DIRECTIVES
The FAA has determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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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:
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:
■ a. Removing Airworthiness Directive
(AD) 2015–12–03, Amendment 39–
18176 (80 FR 34252, June 16, 2015), and
■ b. Adding the following new AD:
■
The Boeing Company: Docket No. FAA–
2022–0148; Project Identifier AD–2021–
00922–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by May 9,
2022.
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Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules
(b) Affected ADs
This AD replaces AD 2015–12–03,
Amendment 39–18176 (80 FR 34252, June
16, 2015) (AD 2015–12–03).
(c) Applicability
This AD applies to The Boeing Company
airplanes, certificated in any category,
identified in paragraphs (c)(1) and (2) of this
AD.
(1) All Model 777–200, –200LR, –300,
–300ER series airplanes.
(2) Model 777F airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before the effective date of this AD.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Unsafe Condition
This AD was prompted by the
manufacturer’s determination that the
procedure for the rudder freeplay inspection
available at the time did not properly detect
excessive freeplay in the rudder control load
loop. This AD was also prompted by
engineering testing that revealed that the
force being applied to the elevator to detect
excessive freeplay was insufficient. The FAA
is issuing this AD to address excessive wear
in the load loop components of the control
surfaces, which could lead to excessive
freeplay of the control surfaces, flutter, and
consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Repetitive Inspections of
Elevators, Rudder, and Rudder Tab, With
Revised Service Information
This paragraph restates the requirements of
paragraph (g) of AD 2015–12–03, with
revised service information. For Model 777–
200, –200LR, –300, and –300ER series
airplanes: At the applicable times specified
in tables 1, 2, and 3 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 777–27–0062, Revision 2,
dated January 27, 2014, or Revision 4, dated
July 15, 2021, except as provided by
paragraph (i)(1) of this AD: Inspect the
freeplay of the right and left elevators,
rudder, and rudder tab by accomplishing all
of the actions specified in Parts 1, 3, and 5
of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–27–0062, Revision 2, dated January 27,
2014, or Revision 4, dated July 15, 2021,
except as provided by paragraphs (i)(2)
through (4) of this AD. Repeat the inspections
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thereafter at the intervals specified in tables
1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Special Attention Service Bulletin
777–27–0062, Revision 2, dated January 27,
2014, or Revision 4, dated July 15, 2021. If,
during any inspection required by this
paragraph, the freeplay exceeds any
applicable measurement specified in Part 1,
3, and 5, as applicable, of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–27–
0062, Revision 2, dated January 27, 2014, or
Revision 4, dated July 15, 2021, before
further flight, do the applicable corrective
actions in accordance with Part 1, 3, and 5
of the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–27–0062, Revision 2, dated January 27,
2014, or Revision 4, dated July 15, 2021.
After the effective date of this AD use only
Boeing Special Attention Service Bulletin
777–27–0062, Revision 4, dated July 15,
2021.
(h) Retained Repetitive Lubrication, With
Revised Service Information
This paragraph restates the requirements of
paragraph (h) of AD 2015–12–03, with
revised service information. For Model 777–
200, –200LR, –300, –300ER series airplanes:
At the applicable times specified in tables 1,
2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
777–27–0062, Revision 2, dated January 27,
2014, or Revision 4, dated July 15, 2021,
except as provided by paragraph (i)(1) of this
AD: Lubricate the elevator components,
rudder components, and rudder tab
components, by accomplishing all of the
actions specified in Parts 2, 4, and 6 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–27–
0062, Revision 2, dated January 27, 2014, or
Revision 4, dated July 15, 2021. Repeat the
lubrication thereafter at the interval specified
in tables 1, 2, and 3 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 777–27–0062, Revision 2,
dated January 27, 2014, or Revision 4, dated
July 15, 2021. After the effective date of this
AD use only Boeing Special Attention
Service Bulletin 777–27–0062, Revision 4,
dated July 15, 2021.
(i) Retained Exceptions to Service
Information Specifications, With Revised
Service Information
This paragraph restates the requirements of
paragraph (i) of AD 2015–12–03, with revised
service information, for Model 777–200,
–200LR, –300, –300ER series airplanes.
(1) Where Boeing Special Attention Service
Bulletin 777–27–0062, Revision 2, dated
January 27, 2014, and Revision 4, dated July
15, 2021, specify a compliance time ‘‘after
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16657
the original issue date on this service
bulletin,’’ this AD requires compliance
within the specified compliance time after
July 25, 2007 (the effective date of AD 2007–
13–05, Amendment 39–15109 (72 FR 33856,
June 20, 2007)). After the effective date of
this AD, only Boeing Special Attention
Service Bulletin 777–27–0062, Revision 4,
dated July 15, 2021, may be used.
(2) Where Appendix B, paragraph 1.f.,
‘‘Freeplay Inspection,’’ step (8), of Boeing
Special Attention Service Bulletin 777–27–
0062, Revision 2, dated January 27, 2014,
specifies that the center of the pad must be
within 1.0 inch (13 millimeters) of the center
line of the rib rivets in the rudder tab, this
AD requires that the center of the tab must
be within 1.0 inch (25 millimeters) of the
center line of the rib rivets in the rudder tab.
(3) Where Appendix C, paragraph 1.e.,
‘‘Rudder Tab Surface Freeplay—Inspection,’’
step (2) and step (6), of Boeing Special
Attention Service Bulletin 777–27–0062,
Revision 2, dated January 27, 2014, specify
that the placement of the force gage and pad
should be within one inch of the centerline
line of the middle rudder PCU rib and at 12
+/¥1 inch (305 +/¥72 millimeters) forward
of the rudder tab trailing edge, this AD
requires placement of the force gage and pad
within one inch of the centerline line of the
middle rudder PCU rib and at 12 +/¥1 inch
(305 +/¥25 millimeters) forward of the
rudder tab trailing edge.
(4) Where Appendix C, paragraph 1.e.,
‘‘Rudder Tab Surface Freeplay—Inspection,’’
step (3), of Boeing Special Attention Service
Bulletin 777–27–0062, Revision 2, dated
January 27, 2014, specifies to apply a 30 +/
¥pound (133 +/¥14 newton) force, this AD
requires applying a 30 +/¥3 pound force
(133 +/¥14 newton) force.
(j) New Maintenance or Inspection Program
Revision
For Model 777F airplanes: Within 30 days
after the effective date of this AD, revise the
777F elevator freeplay maintenance
procedure in the existing maintenance or
inspection program, as applicable, by doing
the actions specified in paragraphs (j)(1)
through (3) of this AD.
(1) Remove the existing hydraulic
depressurization PCU test setup procedure
step and replace it by incorporating the
information specified in figure 1 to paragraph
(j) of this AD.
(2) Revise the jack test force used to push
the elevator up to 225 +/¥10 lb (102.1 +/
¥4.5 kg).
(3) Revise the elevator freeplay dial
indicator limit to 0.34 in. (152 mm) or less.
E:\FR\FM\24MRP1.SGM
24MRP1
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Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules
Figure 1 to paragraph G): Circuit breaker elevator freeplay test setup
Do these steps to prepare for the freeplay inspection:
NOTE: Each PCU can be inspected in any order, as long as the setup for the inspection
is performed per the steps below.
a)
To inspect the left elevator outboard PCU, do these steps:
1. Open this circuit breaker and install safety tag:
Power Supply Assembly Center, M24301
Row
Col
Number
Name
b)
A
7
CBA7-C
ELEV PCU
2. Make sure that the left elevator inboard PCU is in bypass mode
To inspect the left elevator inboard PCU, do these steps:
1. Open this circuit breaker and install safety tag:
Power Supply Assembly Left, M24101
Row
Col
Number
Name
c)
A
7
CBA7-L
ELEV PCU
2. Make sure that the left elevator outboard PCU is in bypass mode.
To inspect the right elevator inboard PCU, do these steps:
1. Open this circuit breaker and install safety tag:
Left Power Management Panel, P110
Row
Col
Number
Name
K
27
C27609
ELEV PCU RIB (BLK)/ROB(BYP)
2. Make sure that the right elevator outboard PCU is in bypass mode.
d) To inspect the right elevator outboard PCU, do these steps:
1. Open this circuit breaker and install safety tag:
Power Supply Assembly Right, M24201
Row
Col
Number
Name
A
7
CBA7-R
ELEV PCU
Make sure that the right elevator inboard PCU is in bypass mode.
Note 1 to paragraph (j): Refer to AMM task
27–31–09–200–801, dated September 5,
2021, for additional guidance.
khammond on DSKJM1Z7X2PROD with PROPOSALS
(k) No Alternative Actions or Intervals
After the existing maintenance or
inspection program has been revised as
required by paragraph (j) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (m) of this AD.
(l) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using
Boeing Special Attention Service Bulletin
777–27–0062, Revision 3, dated October 9,
2015.
(m) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
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
VerDate Sep<11>2014
16:36 Mar 23, 2022
Jkt 256001
principal inspector or responsible Flight
Standards Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (n)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-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 responsible Flight Standards Office
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair
method, modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for the
freeplay measurements of the right and left
rudder tab required by AD 2015–12–03, are
approved as AMOCs for the corresponding
provisions of this AD.
(5) AMOCs approved previously for the
freeplay measurements of the rudder
required by AD 2015–12–03, are approved as
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
AMOCs for the corresponding provisions of
this AD.
(6) AMOCs approved previously for the
repetitive lubrications required by AD 2015–
12–03, are approved as AMOCs for the
corresponding provisions of this AD.
(n) Related Information
(1) For more information about this AD,
contact Luis Cortez-Muniz, Aerospace
Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: (206)
231–3958; email: Luis.A.Cortez-Muniz@
faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
E:\FR\FM\24MRP1.SGM
24MRP1
EP24MR22.059</GPH>
2.
Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules
Issued on February 18, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[Docket No. FAA–2022–0292; Project
Identifier AD–2021–01297–E]
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact International Aero
Engines, LLC, 400 Main Street, East
Hartford, CT 06118; phone: (860) 690–
9667; email: help24@pw.utc.com;
website: https://fleetcare.prattwhitney.
com. You may view this service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call (817) 222–5110.
RIN 2120–AA64
Examining the AD Docket
[FR Doc. 2022–05691 Filed 3–23–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; International
Aero Engines, LLC Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain International Aero Engines, LLC
(IAE LLC) PW1122G–JM, PW1124G1–
JM, PW1124G–JM, PW1127G1–JM,
PW1127GA–JM, PW1127G–JM,
PW1129G–JM, PW1130G–JM,
PW1133GA–JM, and PW1133G–JM
model turbofan engines. This proposed
AD was prompted by an analysis of an
event involving an International Aero
Engines AG (IAE AG) V2533–A5 model
turbofan engine, which experienced an
uncontained failure of a high-pressure
turbine (HPT) 1st-stage disk that
resulted in high-energy debris
penetrating the engine cowling. This
proposed AD would require
performance of an ultrasonic inspection
(USI) of the HPT 1st-stage disk and HPT
2nd-stage disk and, depending on the
results of the inspections, replacement
of the HPT 1st-stage disk or HPT 2ndstage disk. The FAA is proposing this
AD to address the unsafe condition on
these products.
DATES: The FAA must receive comments
on this proposed AD by May 9, 2022.
ADDRESSES: 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
khammond on DSKJM1Z7X2PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:36 Mar 23, 2022
Jkt 256001
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2022–0292; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
NPRM, any comments received, and
other information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Mark Taylor, Aviation Safety Engineer,
ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone:
(781) 238–7229; email: Mark.Taylor@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2022–0292; Project Identifier AD–
2021–01297–E’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
16659
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Mark Taylor, Aviation
Safety Engineer, ECO Branch, FAA,
1200 District Avenue, Burlington, MA
01803. Any commentary that the FAA
receives which is not specifically
designated as CBI will be placed in the
public docket for this rulemaking.
Background
On March 18, 2020, an Airbus Model
A321–231 airplane, powered by IAE AG
V2533–A5 model turbofan engines,
experienced an uncontained HPT 1ststage disk failure that resulted in highenergy debris penetrating the engine
cowling. Based on a preliminary
analysis of this event, on March 21,
2020, the FAA issued Emergency AD
2020–07–51 (followed by publication in
the Federal Register on April 13, 2020,
as a Final Rule, Request for Comments
(85 FR 20402)), which requires the
removal from service of certain HPT 1ststage disks installed on IAE AG V2522–
A5, V2524–A5, V2525–D5, V2527–A5,
V2527E–A5, V2527M–A5, V2528–D5,
V2530–A5, and V2533–A5 model
turbofan engines.
Based on the root cause analysis
performed since that March 2020 event,
Pratt & Whitney (PW) identified a
different population of HPT 1st-stage
disks and HPT 2nd-stage disks that are
subject to the same unsafe condition
identified in AD 2020–07–51. In
response, the FAA issued AD 2021–19–
10 on September 10, 2021 (86 FR
50610), which requires the removal
from service of certain HPT 1st-stage
disks and HPT 2nd-stage disks installed
on IAE LLC PW1122G–JM, PW1124G1–
JM, PW1124G–JM, PW1127G1–JM,
PW1127GA–JM, PW1127G–JM,
PW1129G–JM, PW1130G–JM,
PW1133GA–JM, and PW1133G–JM
model turbofan engines.
Since the FAA issued AD 2021–19–
10, PW identified another
subpopulation of HPT 1st-stage disks
and HPT 2nd-stage disks that require
inspection and possible removal from
service. Included in this additional
subpopulation of HPT 1st-stage disks
E:\FR\FM\24MRP1.SGM
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]]>Agencies
[Federal Register Volume 87, Number 57 (Thursday, March 24, 2022)]
[Proposed Rules]
[Pages 16654-16659]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-05691]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0148; Project Identifier AD-2021-00922-T]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2015-12-03, which applies to certain The Boeing Company Model 777-200,
-200LR, -300, and -300ER series airplanes. AD 2015-12-03 requires
repetitive freeplay inspections and lubrication of the right and left
[[Page 16655]]
elevators, rudder, and rudder tab, and related investigative and
corrective actions if necessary. Since the FAA issued AD 2015-12-03,
engineering testing revealed that the force being applied to the
elevator to detect excessive freeplay was insufficient. This proposed
AD would continue to require certain actions in AD 2015-12-03 for
certain airplanes, and would require revising the existing maintenance
or inspection program, as applicable, for certain other airplanes, to
incorporate a revised or new elevator freeplay maintenance procedure,
as applicable. This proposed AD would also add airplanes to the
applicability. The FAA is proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments on this proposed AD by May 9,
2022.
ADDRESSES: 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 NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may
view this service information at the FAA, Airworthiness Products
Section, Operational Safety Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call 206-231-3195. It is also available at https://www.regulations.gov
by searching for and locating Docket No. FAA-2022-0148.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2022-0148; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this NPRM, any comments
received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Luis Cortez-Muniz, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: (206) 231-3958; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2022-0148; Project Identifier
AD-2021-00922-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposed AD.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Luis
Cortez-Muniz, Aerospace Engineer, Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax:
(206) 231-3958; email: [email protected]. Any commentary that
the FAA receives which is not specifically designated as CBI will be
placed in the public docket for this rulemaking.
Background
The FAA issued AD 2015-12-03, Amendment 39-18176 (80 FR 34252, June
16, 2015) (AD 2015-12-03), for certain The Boeing Company Model 777-
200, -200LR, -300, and -300ER series airplanes. AD 2015-12-03 was
prompted by the manufacturer's determination that the procedure for the
rudder freeplay inspection available at the time did not properly
detect excessive freeplay in the rudder control load loop. AD 2015-12-
03 requires repetitive freeplay inspections and lubrication of the
right and left elevators, rudder, and rudder tab, and related
investigative and corrective actions if necessary. The agency issued AD
2015-12-03 to detect and correct excessive wear in the load loop
components of the control surfaces, which could lead to excessive
freeplay of the control surfaces, flutter, and consequent loss of
control of the airplane.
AD 2015-12-03 superseded AD 2007-13-05, Amendment 39-15109 (72 FR
33856, June 20, 2007).
Actions Since AD 2015-12-03 Was Issued
Since the FAA issued AD 2015-12-03, engineering testing revealed
that the force being applied to the elevator to detect excessive
freeplay was insufficient. The original bypass test setup for the power
control unit (PCU), which used a hydraulic depressurization method, was
found to be unreliable for putting the adjacent PCU into bypass mode,
and a new elevator freeplay maintenance procedure is necessary. Model
777F airplanes were not added to the applicability in AD 2015-12-03
because there was a certification maintenance requirement (CMR) task to
accomplish the freeplay inspections for those airplanes; therefore, the
FAA has determined that it is necessary for operators to revise the
maintenance or inspection program to update the elevator freeplay
procedures for Model 777F airplanes.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Special Attention Service Bulletin 777-27-
0062, Revision 4, dated July 15, 2021. This service information
specifies procedures for changing the elevator
[[Page 16656]]
freeplay instructions by adding changes to the input force, elevator
freeplay limit, and PCU bypass test setup.
This proposed AD would also require Boeing Special Attention
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014, which
the Director of the Federal Register approved for incorporation by
reference as of July 21, 2015 (80 FR 34253, June 16, 2015).
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Proposed AD Requirements in This NPRM
This proposed AD would retain certain requirements of AD 2015-12-03
and require accomplishing the actions specified in accordance with
updated service information, including corrective actions, such as
repairs, already described for Model 777-200, -200LR, -300, and -300ER
airplanes. This proposed AD would also add Model 777F series airplanes
to the applicability. For Model 777F series airplanes, this proposed AD
would require revising the existing maintenance or inspection program,
as applicable, to incorporate a new elevator freeplay maintenance
procedure. For information on the procedures and compliance times, see
this service information at https://www.regulations.gov by searching
for and locating Docket No. FAA-2022-0148.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 281 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Required actions Labor cost Parts cost Cost per product operators (218)
----------------------------------------------------------------------------------------------------------------
Measurement (inspection), 4 work-hours x $85 $0 $340 per $74,120 per
elevator. per hour = $340 measurement measurement
per measurement (inspection) cycle. (inspection)
(inspection) cycle. cycle.
Lubrication, elevator............ 17 work-hours x $85 0 $1,445 per $315,010 per
per hour = $1,445 lubrication cycle. lubrication cycle.
per lubrication
cycle.
Measurement (inspection), rudder. 4 work-hours x $85 0 $340 per $74,230 per
per hour = $340 measurement measurement
per measurement (inspection) cycle. (inspection)
(inspection) cycle. cycle.
Lubrication, rudder.............. 7 work-hours x $85 0 $595 per $129,710 per
per hour = $595 lubrication cycle. lubrication cycle.
per lubrication
cycle.
Measurement (inspection), rudder 3 work-hours x $85 0 $255 per $55,590 per
tab. per hour = $255 measurement measurement
per measurement (inspection) cycle. (inspection)
(inspection) cycle. cycle.
Lubrication, rudder tab.......... 5 work-hours x $85 0 $425 per $92,650 per
per hour = $425 lubrication cycle. lubrication cycle.
per lubrication
cycle.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition corrective
actions specified in this proposed AD.
The FAA has determined that revising the existing maintenance or
inspection program takes an average of 90 work-hours per operator,
although the agency recognizes that this number may vary from operator
to operator. Since operators incorporate maintenance or inspection
program changes for their affected fleet(s), the FAA has determined
that a per-operator estimate is more accurate than a per-airplane
estimate. Therefore, the FAA estimates the average total cost per Model
777F operator to be $7,650 (90 work-hours x $85 per work-hour).
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.
The FAA is 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
The FAA has determined that this proposed AD would not have
federalism implications under Executive Order 13132. This proposed AD
would not have a substantial direct effect on the States, on the
relationship between the national Government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive (AD) 2015-12-03, Amendment 39-18176
(80 FR 34252, June 16, 2015), and
0
b. Adding the following new AD:
The Boeing Company: Docket No. FAA-2022-0148; Project Identifier AD-
2021-00922-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by May 9, 2022.
[[Page 16657]]
(b) Affected ADs
This AD replaces AD 2015-12-03, Amendment 39-18176 (80 FR 34252,
June 16, 2015) (AD 2015-12-03).
(c) Applicability
This AD applies to The Boeing Company airplanes, certificated in
any category, identified in paragraphs (c)(1) and (2) of this AD.
(1) All Model 777-200, -200LR, -300, -300ER series airplanes.
(2) Model 777F airplanes with an original airworthiness
certificate or original export certificate of airworthiness issued
on or before the effective date of this AD.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Unsafe Condition
This AD was prompted by the manufacturer's determination that
the procedure for the rudder freeplay inspection available at the
time did not properly detect excessive freeplay in the rudder
control load loop. This AD was also prompted by engineering testing
that revealed that the force being applied to the elevator to detect
excessive freeplay was insufficient. The FAA is issuing this AD to
address excessive wear in the load loop components of the control
surfaces, which could lead to excessive freeplay of the control
surfaces, flutter, and consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections of Elevators, Rudder, and Rudder
Tab, With Revised Service Information
This paragraph restates the requirements of paragraph (g) of AD
2015-12-03, with revised service information. For Model 777-200, -
200LR, -300, and -300ER series airplanes: At the applicable times
specified in tables 1, 2, and 3 of paragraph 1.E., ``Compliance,''
of Boeing Special Attention Service Bulletin 777-27-0062, Revision
2, dated January 27, 2014, or Revision 4, dated July 15, 2021,
except as provided by paragraph (i)(1) of this AD: Inspect the
freeplay of the right and left elevators, rudder, and rudder tab by
accomplishing all of the actions specified in Parts 1, 3, and 5 of
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 777-27-0062, Revision 2, dated January 27, 2014, or
Revision 4, dated July 15, 2021, except as provided by paragraphs
(i)(2) through (4) of this AD. Repeat the inspections thereafter at
the intervals specified in tables 1, 2, and 3 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 777-27-
0062, Revision 2, dated January 27, 2014, or Revision 4, dated July
15, 2021. If, during any inspection required by this paragraph, the
freeplay exceeds any applicable measurement specified in Part 1, 3,
and 5, as applicable, of the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777-27-0062, Revision 2, dated
January 27, 2014, or Revision 4, dated July 15, 2021, before further
flight, do the applicable corrective actions in accordance with Part
1, 3, and 5 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-27-0062, Revision 2, dated January
27, 2014, or Revision 4, dated July 15, 2021. After the effective
date of this AD use only Boeing Special Attention Service Bulletin
777-27-0062, Revision 4, dated July 15, 2021.
(h) Retained Repetitive Lubrication, With Revised Service Information
This paragraph restates the requirements of paragraph (h) of AD
2015-12-03, with revised service information. For Model 777-200, -
200LR, -300, -300ER series airplanes: At the applicable times
specified in tables 1, 2, and 3 of paragraph 1.E., ``Compliance,''
of Boeing Special Attention Service Bulletin 777-27-0062, Revision
2, dated January 27, 2014, or Revision 4, dated July 15, 2021,
except as provided by paragraph (i)(1) of this AD: Lubricate the
elevator components, rudder components, and rudder tab components,
by accomplishing all of the actions specified in Parts 2, 4, and 6
of the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014, or
Revision 4, dated July 15, 2021. Repeat the lubrication thereafter
at the interval specified in tables 1, 2, and 3 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 777-27-
0062, Revision 2, dated January 27, 2014, or Revision 4, dated July
15, 2021. After the effective date of this AD use only Boeing
Special Attention Service Bulletin 777-27-0062, Revision 4, dated
July 15, 2021.
(i) Retained Exceptions to Service Information Specifications, With
Revised Service Information
This paragraph restates the requirements of paragraph (i) of AD
2015-12-03, with revised service information, for Model 777-200, -
200LR, -300, -300ER series airplanes.
(1) Where Boeing Special Attention Service Bulletin 777-27-0062,
Revision 2, dated January 27, 2014, and Revision 4, dated July 15,
2021, specify a compliance time ``after the original issue date on
this service bulletin,'' this AD requires compliance within the
specified compliance time after July 25, 2007 (the effective date of
AD 2007-13-05, Amendment 39-15109 (72 FR 33856, June 20, 2007)).
After the effective date of this AD, only Boeing Special Attention
Service Bulletin 777-27-0062, Revision 4, dated July 15, 2021, may
be used.
(2) Where Appendix B, paragraph 1.f., ``Freeplay Inspection,''
step (8), of Boeing Special Attention Service Bulletin 777-27-0062,
Revision 2, dated January 27, 2014, specifies that the center of the
pad must be within 1.0 inch (13 millimeters) of the center line of
the rib rivets in the rudder tab, this AD requires that the center
of the tab must be within 1.0 inch (25 millimeters) of the center
line of the rib rivets in the rudder tab.
(3) Where Appendix C, paragraph 1.e., ``Rudder Tab Surface
Freeplay--Inspection,'' step (2) and step (6), of Boeing Special
Attention Service Bulletin 777-27-0062, Revision 2, dated January
27, 2014, specify that the placement of the force gage and pad
should be within one inch of the centerline line of the middle
rudder PCU rib and at 12 +/-1 inch (305 +/-72 millimeters) forward
of the rudder tab trailing edge, this AD requires placement of the
force gage and pad within one inch of the centerline line of the
middle rudder PCU rib and at 12 +/-1 inch (305 +/-25 millimeters)
forward of the rudder tab trailing edge.
(4) Where Appendix C, paragraph 1.e., ``Rudder Tab Surface
Freeplay--Inspection,'' step (3), of Boeing Special Attention
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014,
specifies to apply a 30 +/-pound (133 +/-14 newton) force, this AD
requires applying a 30 +/-3 pound force (133 +/-14 newton) force.
(j) New Maintenance or Inspection Program Revision
For Model 777F airplanes: Within 30 days after the effective
date of this AD, revise the 777F elevator freeplay maintenance
procedure in the existing maintenance or inspection program, as
applicable, by doing the actions specified in paragraphs (j)(1)
through (3) of this AD.
(1) Remove the existing hydraulic depressurization PCU test
setup procedure step and replace it by incorporating the information
specified in figure 1 to paragraph (j) of this AD.
(2) Revise the jack test force used to push the elevator up to
225 +/-10 lb (102.1 +/-4.5 kg).
(3) Revise the elevator freeplay dial indicator limit to 0.34
in. (152 mm) or less.
[[Page 16658]]
[GRAPHIC] [TIFF OMITTED] TP24MR22.059
Note 1 to paragraph (j): Refer to AMM task 27-31-09-200-801,
dated September 5, 2021, for additional guidance.
(k) No Alternative Actions or Intervals
After the existing maintenance or inspection program has been
revised as required by paragraph (j) of this AD, no alternative
actions (e.g., inspections) or intervals may be used unless the
actions or intervals are approved as an alternative method of
compliance (AMOC) in accordance with the procedures specified in
paragraph (m) of this AD.
(l) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Boeing Special Attention
Service Bulletin 777-27-0062, Revision 3, dated October 9, 2015.
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, 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 responsible Flight Standards Office,
as appropriate. If sending information directly to the manager of
the certification office, send it to the attention of the person
identified in paragraph (n)(1) of this AD. Information may be
emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair
method, modification deviation, or alteration deviation must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for the freeplay measurements of
the right and left rudder tab required by AD 2015-12-03, are
approved as AMOCs for the corresponding provisions of this AD.
(5) AMOCs approved previously for the freeplay measurements of
the rudder required by AD 2015-12-03, are approved as AMOCs for the
corresponding provisions of this AD.
(6) AMOCs approved previously for the repetitive lubrications
required by AD 2015-12-03, are approved as AMOCs for the
corresponding provisions of this AD.
(n) Related Information
(1) For more information about this AD, contact Luis Cortez-
Muniz, Aerospace Engineer, Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax:
(206) 231-3958; email: [email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des Moines, WA. For information
on the availability of this material at the FAA, call 206-231-3195.
[[Page 16659]]
Issued on February 18, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-05691 Filed 3-23-22; 8:45 am]
BILLING CODE 4910-13-P
