Airworthiness Directives; The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 48620-48623 [2010-19834]
Download as PDF
<![CDATA[
48620
Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules
this proposed AD. See the AD docket to
examine the economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend part
39 of the Federal Aviation Regulations
(14 CFR part 39) as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
jlentini on DSKJ8SOYB1PROD with PROPOSALS
2. Section 39.13 is amended by
adding a new airworthiness directive to
read as follows:
Eurocopter France: Docket No. FAA–2010–
0781; Directorate Identifier 2007–SW–
49–AD.
Applicability: Model AS–365N2, AS 365
N3, and SA–365N1 helicopters, with an
aluminum tail rotor (T/R) blade pitch control
shaft, part number (P/N) 365A33.6161.20 or
P/N 365A33.6161.21, installed, certificated in
any category.
Compliance: Required within 100 hours
time-in-service, unless accomplished
previously.
To prevent failure of the T/R blade pitch
control shaft, loss of T/R control, and
subsequent loss of control of the helicopter,
accomplish the following:
(a) Remove the aluminum T/R blade pitch
control shaft, P/N 365A33.6161.20 or P/N
365A33.6161.21, and replace it with a steel
VerDate Mar<15>2010
16:23 Aug 10, 2010
Jkt 220001
Note: The subject of this AD is addressed
in European Aviation Safety Agency AD No.
2007–0220, dated August 13, 2007.
Issued in Fort Worth, Texas, on August 2,
2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2010–19823 Filed 8–10–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0761; Directorate
Identifier 2010–NM–069–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
1. The authority citation for part 39
continues to read as follows:
§ 39.13
T/R blade pitch control shaft, P/N
365A33.6214.20, in accordance with the
Accomplishment Instructions, Operational
Procedure, paragraphs 2.B.1. through 2.B.3.,
of Eurocopter Alert Service Bulletin No.
01.00.59, dated June 21, 2007.
(b) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Safety
Management Group, Rotorcraft Directorate,
FAA, ATTN: Jim Grigg, Aviation Safety
Engineer, 2601 Meacham Blvd., Fort Worth,
Texas 76137, telephone (817) 222–5126, fax
(817) 222–5961.
(c) The Joint Aircraft System/Component
(JASC) Code is 6500: Tail Rotor Drive
System.
We propose to adopt a new
airworthiness directive (AD) for certain
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. This
proposed AD would require installing
two warning level indicator lights on
the P2–2 center instrument panel in the
flight compartment for certain airplanes.
For a certain other airplane, this
proposed AD would require activating
the cabin altitude warning and takeoff
configuration warning lights. For all
airplanes, this proposed AD also would
require revising the airplane flight
manual to remove certain requirements
included by previous AD actions, to
require new pressure altitude
limitations for certain airplanes, and to
advise the flightcrew of the following
changes: revised emergency procedures
to use when a cabin altitude warning or
SUMMARY:
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
rapid depressurization occurs, and
revised cabin pressurization procedures
for normal operations. This proposed
AD results from a design change in the
cabin altitude warning system that
would address the identified unsafe
condition. We are proposing this AD to
prevent failure of the flightcrew to
recognize and react to a valid cabin
altitude warning horn, which could
result in incapacitation of the flightcrew
due to hypoxia (lack of oxygen in body),
and consequent loss of control of the
airplane.
DATES: We must receive comments on
this proposed AD by September 27,
2010.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
E:\FR\FM\11AUP1.SGM
11AUP1
Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules
FOR FURTHER INFORMATION CONTACT:
Jeffrey W. Palmer, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6472; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
jlentini on DSKJ8SOYB1PROD with PROPOSALS
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2010–0761; Directorate Identifier
2010–NM–069–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The Model 737 cabin altitude warning
is an intermittent horn that sounds
when cabin altitude exceeds 10,000 feet.
The same intermittent warning horn
sound is utilized by the takeoff
configuration warning system (TCWS)
to warn of unsafe airplane configuration
for takeoff. The TCWS warning
functionality is inhibited by air/ground
logic when the airplane is in flight.
However, the Model 737 cabin altitude
warning system design does not
currently incorporate a dedicated means
of positively identifying the warning
horn as a cabin altitude warning or a
takeoff configuration warning. There are
approximately 25 known instances
where flightcrews have misinterpreted a
valid cabin altitude warning as a takeoff
configuration warning.
Failure of the flightcrew to recognize
and react to a valid cabin altitude
warning horn could result in
incapacitation of the flightcrew due to
hypoxia (lack of oxygen in body), and
consequent loss of control of the
airplane. To address this unsafe
condition, we issued the following ADs.
On November 7, 2003, we issued
related AD 2003–03–15 R1, Amendment
39–13366 (68 FR 64802, November 17,
2003), for various The Boeing Company
and McDonnell Douglas Corporation
VerDate Mar<15>2010
16:23 Aug 10, 2010
Jkt 220001
transport category airplanes. That AD
requires revising the airplane flight
manual (AFM) to advise the flightcrew
to don oxygen masks as a first and
immediate step when the cabin altitude
warning occurs. We issued that AD to
prevent incapacitation of the flightcrew
due to lack of oxygen, which could
result in loss of control of the airplane.
On June 15, 2006, we issued related
AD 2006–13–13, Amendment 39–14666
(71 FR 35781, June 22, 2006). (A
correction of that AD was published in
the Federal Register on July 3, 2006 (71
FR 37980).) That AD applies to all
Model 737 airplanes. That AD requires
revising the AFM to advise the
flightcrew of improved procedures for
pre-flight setup of the cabin
pressurization system, as well as
improved procedures for interpreting
and responding to the cabin altitude/
configuration warning horn. That AD
resulted from reports that airplanes had
failed to pressurize, and that the
flightcrews failed to react properly to
the cabin altitude warning horn. We
issued that AD to prevent failure of the
airplane to pressurize and subsequent
failure of the flightcrew to recognize and
react to a valid cabin altitude warning
horn, which could result in
incapacitation of the flightcrew due to
hypoxia (lack of oxygen in body) and
consequent loss of airplane control.
On October 24, 2008, we issued
related AD 2008–23–07, Amendment
39–15728 (73 FR 66512, November 10,
2008), for all Model 737 airplanes. That
AD requires revising the AFM to
include a new flightcrew briefing that
must be done before the first flight of
the day and following any change in
flightcrew members, and to advise the
flightcrew of this additional briefing.
That AD resulted from continuing
reports that flightcrews have failed to
recognize and react properly to the
cabin altitude warning horn. We issued
that AD to prevent failure of the
flightcrew to recognize and react
properly to a valid cabin altitude
warning horn, which could result in
incapacitation of the flightcrew due to
hypoxia (lack of oxygen in body) and
consequent loss of airplane control.
The preambles to AD 2006–13–13 and
AD 2008–23–07 explain that the
revisions to the AFM required by those
ADs are considered to be interim action.
The manufacturer had advised us that it
was developing a design change in the
cabin altitude warning system that
would address the identified unsafe
condition(s), and that once this design
change was developed, approved, and
available, the FAA might consider
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
48621
additional rulemaking. The
manufacturer now has developed such a
modification, and we have determined
that further rulemaking is necessary;
this proposed AD follows from that
determination. We can better ensure
long-term continued operational safety
by modifications or design changes to
remove the source of the problem, rather
than by AFM revisions alone.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–31A1325, dated
January 11, 2010 (for Model 737–100,
–200, –200C, –300, –400, and –500
series airplanes). This service bulletin
describes procedures for installing two
warning level indicator lights on the
P2–2 center instrument panel in the
flight compartment. This installation
includes changing three wire bundles.
We have also reviewed Boeing Alert
Service Bulletin 737–31A1398, dated
January 7, 2010 (for Model 737–400
series airplane, variable number
PW234). This service bulletin describes
procedures for activating the cabin
altitude warning and takeoff
configuration warning lights. The
activation includes changing the wiring
in the W066 wire bundle and removing
the INOP markers from the cabin
altitude warning and takeoff
configuration warning lights.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design. This proposed AD would
require accomplishing the actions
specified in the service information
described previously. The proposed AD
would also require revising the AFM to
remove certain requirements included
by previous AD actions, to require new
pressure altitude limitations for certain
airplanes, and to advise the flightcrew
of the following changes: revised
emergency procedures to use when a
cabin altitude warning or rapid
depressurization occurs, and revised
cabin pressurization procedures for
normal operations.
Costs of Compliance
We estimate that this proposed AD
would affect 741 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD.
E:\FR\FM\11AUP1.SGM
11AUP1
48622
Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules
TABLE—ESTIMATED COSTS
Action
Installation of warning indicator lights ......
Activation of the cabin altitude warning
system/takeoff configuration warning
lights .....................................................
AFM revision ............................................
jlentini on DSKJ8SOYB1PROD with PROPOSALS
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Jkt 220001
Fleet cost
$85
$2,738
$4,438
740
$3,284,120
1
1
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
16:23 Aug 10, 2010
Number
of U.S.registered
airplanes
Cost per
product
Parts
20
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
VerDate Mar<15>2010
Average
labor rate
per hour
Work hours
85
85
0
0
85
85
1
741
85
62,985
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
failure of the flightcrew to recognize and
react properly to a valid cabin altitude
warning horn, which could result in
incapacitation of the flightcrew due to
hypoxia (lack of oxygen in body) and
consequent loss of airplane control.
PART 39—AIRWORTHINESS
DIRECTIVES
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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 AD:
The Boeing Company: Docket No. FAA–
2010–0761; Directorate Identifier 2010–
NM–069–AD.
Comments Due Date
(a) We must receive comments by
September 27, 2010.
Affected ADs
(b) This AD affects the ADs identified in
paragraphs (b)(1), (b)(2), and (b)(3) of this AD.
This AD does not supersede the requirements
of these ADs.
(1) AD 2008–23–07, Amendment 39–
15728.
(2) AD 2006–13–13, Amendment 39–
14666.
(3) AD 2003–03–15 R1, Amendment 39–
13366.
Applicability
(c) This AD applies to the airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) The Boeing Company Model 737–100,
–200, –200C, –300, –400, and –500 series
airplanes identified in Boeing Alert Service
Bulletin 737–31A1325, dated January 11,
2010.
(2) The Boeing Company Model 737–400
series airplanes identified in Boeing Alert
Service Bulletin 737–31A1398, dated January
7, 2010.
Subject
(d) Air Transport Association (ATA) of
America Code 31: Instruments.
Unsafe Condition
(e) This AD results from a design change
in the cabin altitude warning system that
would address the identified unsafe
condition. The Federal Aviation
Administration is issuing this AD to prevent
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
Installation of Warning Indicator Lights
(g) For airplanes identified in Boeing Alert
Service Bulletin 737–31A1325, dated January
11, 2010: Within 36 months after the effective
date of this AD, install two warning level
indicator lights on the P2–2 center
instrument panel in the flight compartment,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–31A1325, dated January 11, 2010.
Activation of Warning Indicator Lights
(h) For airplanes identified in Boeing Alert
Service Bulletin 737–31A1398, dated January
7, 2010: Within 36 months after the effective
date of this AD, activate the cabin altitude
warning and takeoff configuration warning
lights, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–31A1398, dated January
7, 2010.
Airplane Flight Manual (AFM) Revisions
(i) Before further flight after doing the
installation or activation of the warning
lights required by paragraph (g) or (h) of this
AD, do the actions specified in paragraphs
(i)(1), (i)(2), and (i)(3) of this AD.
(1) Revise the Limitations Section of the
applicable Boeing 737 AFM by doing the
actions specified in paragraphs (i)(1)(i) and
(i)(1)(ii) of this AD.
(i) Delete the ‘‘CABIN ALTITUDE
WARNING TAKEOFF BRIEFING’’ added by
AD 2008–23–07.
(ii) Add the following statement. This may
be done by inserting a copy of this AD into
the applicable AFM.
‘‘For airplanes approved for maximum
takeoff and landing altitudes above 8,400 feet
pressure altitude, change the limitation for
Maximum Takeoff and Landing pressure
altitude as follows: With the CABIN
ALTITUDE and TAKEOFF CONFIG lights
installed and operative on those airplanes
without the High Altitude Landing switch
installed, maximum takeoff and landing
altitude is limited to 9,000 feet pressure
altitude.’’
E:\FR\FM\11AUP1.SGM
11AUP1
Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules
(2) Revise the Emergency Procedures
Section of the applicable Boeing 737 AFM by
doing the actions specified in paragraphs
(i)(2)(i), (i)(2)(ii), (i)(2)(iii), and (i)(2)(iv) of
this AD.
(i) Delete the procedure ‘‘WARNING
HORN—CABIN ALTITUDE OR
CONFIGURATION’’ added by AD 2006–13–
13.
(ii) Delete the procedure entitled ‘‘CABIN
ALTITUDE WARNING OR RAPID
DEPRESSURIZATION’’ added by AD 2006–
13–13.
(iii) If the procedure entitled ‘‘CABIN
ALTITUDE (Airplanes with the CABIN
ALTITUDE lights installed)’’ is currently
contained in the applicable Boeing 737 AFM,
delete the procedure entitled ‘‘CABIN
ALTITUDE (Airplanes with the CABIN
ALTITUDE lights installed).’’
(iv) Add the following statement. This may
be done by inserting a copy of this AD into
the applicable AFM.
‘‘CABIN ALTITUDE WARNING OR RAPID
DEPRESSURIZATION (required by this ad)
Condition: The CABIN ALTITUDE warning
light illuminates or the intermittent warning
horn sounds in flight above 10,000 ft MSL.
RECALL:
Oxygen Masks and Regulators.
Crew Communications .......
REFERENCE:
Pressurization Mode Selector.
Outflow Valve Switch ........
Passenger Oxygen (If Required).
Descent (If Required) ..........
On, 100%
Establish
Manual
Close
On
jlentini on DSKJ8SOYB1PROD with PROPOSALS
Issued in Renton, Washington, on July 28,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
BILLING CODE 4910–13–P
Terminating Action for Affected ADs
(j) Accomplishment of the requirements of
this AD terminates the specified
requirements of the ADs identified in
paragraphs (j)(1), (j)(2), and (j)(3) of this AD,
for only the airplanes identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) AD 2008–23–07: All requirements of
that AD.
(2) AD 2006–13–13: All requirements of
that AD.
(3) AD 2003–03–15 R1: The requirements
specified in paragraph (a), Table 2, and
Figures 2 and 3 of that AD.
16:23 Aug 10, 2010
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Jeffrey W. Palmer, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6472; fax
(425) 917–6590. Information may be e-mailed
to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
[FR Doc. 2010–19834 Filed 8–10–10; 8:45 am]
Initiate
(3) Revise the Normal Procedures Section
of the applicable Boeing 737 AFM by doing
the actions specified in paragraphs (i)(3)(i)
and (i)(3)(ii) of this AD.
(i) Delete the ‘‘CABIN ALTITUDE
WARNING TAKEOFF BRIEFING’’ procedure
added by AD 2008–23–07.
(ii) Add the following statement. This may
be done by inserting a copy of this AD into
the applicable AFM.
‘‘For normal operations, the pressurization
mode selector should be in AUTO prior to
takeoff. (Required by this AD)’’
Note 1: When statements identical to those
specified in paragraphs (i)(1)(ii), (i)(2)(iv),
and (i)(3)(ii) of this AD have been included
in the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copies of this AD may be
removed from the AFM.
VerDate Mar<15>2010
Special Flight Permit
(k) Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
Jkt 220001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0796; Directorate
Identifier 2010–NM–007–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 767–300 Series
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Model 767–300 series airplanes. This
proposed AD would require repetitive
inspections for cracks in the fuselage
skin and backup structure at the lower
very high frequency (VHF) antenna
cutout at station 1197 + 99 between
stringers 39L and 39R, and corrective
actions if necessary. Certain repairs
would terminate certain inspection
requirements. This proposed AD results
SUMMARY:
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
48623
from reports of cracking found in the
section 46 fuselage lower skin around
the periphery of the VHF antenna
baseplate at station 1197 + 99. We are
proposing this AD to detect and correct
fatigue cracks in the fuselage skin and
internal backup structure, which could
result in rapid decompression of the
airplane.
We must receive comments on
this proposed AD by September 27,
2010.
DATES:
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton,
E:\FR\FM\11AUP1.SGM
11AUP1
]]>Agencies
[Federal Register Volume 75, Number 154 (Wednesday, August 11, 2010)]
[Proposed Rules]
[Pages 48620-48623]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-19834]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0761; Directorate Identifier 2010-NM-069-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-100, -200,
-200C, -300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. This proposed AD would require installing two warning level
indicator lights on the P2-2 center instrument panel in the flight
compartment for certain airplanes. For a certain other airplane, this
proposed AD would require activating the cabin altitude warning and
takeoff configuration warning lights. For all airplanes, this proposed
AD also would require revising the airplane flight manual to remove
certain requirements included by previous AD actions, to require new
pressure altitude limitations for certain airplanes, and to advise the
flightcrew of the following changes: revised emergency procedures to
use when a cabin altitude warning or rapid depressurization occurs, and
revised cabin pressurization procedures for normal operations. This
proposed AD results from a design change in the cabin altitude warning
system that would address the identified unsafe condition. We are
proposing this AD to prevent failure of the flightcrew to recognize and
react to a valid cabin altitude warning horn, which could result in
incapacitation of the flightcrew due to hypoxia (lack of oxygen in
body), and consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by September 27,
2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
[[Page 48621]]
FOR FURTHER INFORMATION CONTACT: Jeffrey W. Palmer, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6472; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0761;
Directorate Identifier 2010-NM-069-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The Model 737 cabin altitude warning is an intermittent horn that
sounds when cabin altitude exceeds 10,000 feet. The same intermittent
warning horn sound is utilized by the takeoff configuration warning
system (TCWS) to warn of unsafe airplane configuration for takeoff. The
TCWS warning functionality is inhibited by air/ground logic when the
airplane is in flight. However, the Model 737 cabin altitude warning
system design does not currently incorporate a dedicated means of
positively identifying the warning horn as a cabin altitude warning or
a takeoff configuration warning. There are approximately 25 known
instances where flightcrews have misinterpreted a valid cabin altitude
warning as a takeoff configuration warning.
Failure of the flightcrew to recognize and react to a valid cabin
altitude warning horn could result in incapacitation of the flightcrew
due to hypoxia (lack of oxygen in body), and consequent loss of control
of the airplane. To address this unsafe condition, we issued the
following ADs.
On November 7, 2003, we issued related AD 2003-03-15 R1, Amendment
39-13366 (68 FR 64802, November 17, 2003), for various The Boeing
Company and McDonnell Douglas Corporation transport category airplanes.
That AD requires revising the airplane flight manual (AFM) to advise
the flightcrew to don oxygen masks as a first and immediate step when
the cabin altitude warning occurs. We issued that AD to prevent
incapacitation of the flightcrew due to lack of oxygen, which could
result in loss of control of the airplane.
On June 15, 2006, we issued related AD 2006-13-13, Amendment 39-
14666 (71 FR 35781, June 22, 2006). (A correction of that AD was
published in the Federal Register on July 3, 2006 (71 FR 37980).) That
AD applies to all Model 737 airplanes. That AD requires revising the
AFM to advise the flightcrew of improved procedures for pre-flight
setup of the cabin pressurization system, as well as improved
procedures for interpreting and responding to the cabin altitude/
configuration warning horn. That AD resulted from reports that
airplanes had failed to pressurize, and that the flightcrews failed to
react properly to the cabin altitude warning horn. We issued that AD to
prevent failure of the airplane to pressurize and subsequent failure of
the flightcrew to recognize and react to a valid cabin altitude warning
horn, which could result in incapacitation of the flightcrew due to
hypoxia (lack of oxygen in body) and consequent loss of airplane
control.
On October 24, 2008, we issued related AD 2008-23-07, Amendment 39-
15728 (73 FR 66512, November 10, 2008), for all Model 737 airplanes.
That AD requires revising the AFM to include a new flightcrew briefing
that must be done before the first flight of the day and following any
change in flightcrew members, and to advise the flightcrew of this
additional briefing. That AD resulted from continuing reports that
flightcrews have failed to recognize and react properly to the cabin
altitude warning horn. We issued that AD to prevent failure of the
flightcrew to recognize and react properly to a valid cabin altitude
warning horn, which could result in incapacitation of the flightcrew
due to hypoxia (lack of oxygen in body) and consequent loss of airplane
control.
The preambles to AD 2006-13-13 and AD 2008-23-07 explain that the
revisions to the AFM required by those ADs are considered to be interim
action. The manufacturer had advised us that it was developing a design
change in the cabin altitude warning system that would address the
identified unsafe condition(s), and that once this design change was
developed, approved, and available, the FAA might consider additional
rulemaking. The manufacturer now has developed such a modification, and
we have determined that further rulemaking is necessary; this proposed
AD follows from that determination. We can better ensure long-term
continued operational safety by modifications or design changes to
remove the source of the problem, rather than by AFM revisions alone.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-31A1325, dated
January 11, 2010 (for Model 737-100, -200, -200C, -300, -400, and -500
series airplanes). This service bulletin describes procedures for
installing two warning level indicator lights on the P2-2 center
instrument panel in the flight compartment. This installation includes
changing three wire bundles.
We have also reviewed Boeing Alert Service Bulletin 737-31A1398,
dated January 7, 2010 (for Model 737-400 series airplane, variable
number PW234). This service bulletin describes procedures for
activating the cabin altitude warning and takeoff configuration warning
lights. The activation includes changing the wiring in the W066 wire
bundle and removing the INOP markers from the cabin altitude warning
and takeoff configuration warning lights.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously. The proposed AD would
also require revising the AFM to remove certain requirements included
by previous AD actions, to require new pressure altitude limitations
for certain airplanes, and to advise the flightcrew of the following
changes: revised emergency procedures to use when a cabin altitude
warning or rapid depressurization occurs, and revised cabin
pressurization procedures for normal operations.
Costs of Compliance
We estimate that this proposed AD would affect 741 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
[[Page 48622]]
Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average labor Cost per U.S.-
Action Work hours rate per hour Parts product registered Fleet cost
airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Installation of warning indicator lights................ 20 $85 $2,738 $4,438 740 $3,284,120
Activation of the cabin altitude warning system/takeoff 1 85 0 85 1 85
configuration warning lights...........................
AFM revision............................................ 1 85 0 85 741 62,985
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
The Boeing Company: Docket No. FAA-2010-0761; Directorate Identifier
2010-NM-069-AD.
Comments Due Date
(a) We must receive comments by September 27, 2010.
Affected ADs
(b) This AD affects the ADs identified in paragraphs (b)(1),
(b)(2), and (b)(3) of this AD. This AD does not supersede the
requirements of these ADs.
(1) AD 2008-23-07, Amendment 39-15728.
(2) AD 2006-13-13, Amendment 39-14666.
(3) AD 2003-03-15 R1, Amendment 39-13366.
Applicability
(c) This AD applies to the airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) The Boeing Company Model 737-100, -200, -200C, -300, -400,
and -500 series airplanes identified in Boeing Alert Service
Bulletin 737-31A1325, dated January 11, 2010.
(2) The Boeing Company Model 737-400 series airplanes identified
in Boeing Alert Service Bulletin 737-31A1398, dated January 7, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 31:
Instruments.
Unsafe Condition
(e) This AD results from a design change in the cabin altitude
warning system that would address the identified unsafe condition.
The Federal Aviation Administration is issuing this AD to prevent
failure of the flightcrew to recognize and react properly to a valid
cabin altitude warning horn, which could result in incapacitation of
the flightcrew due to hypoxia (lack of oxygen in body) and
consequent loss of airplane control.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Installation of Warning Indicator Lights
(g) For airplanes identified in Boeing Alert Service Bulletin
737-31A1325, dated January 11, 2010: Within 36 months after the
effective date of this AD, install two warning level indicator
lights on the P2-2 center instrument panel in the flight
compartment, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-31A1325, dated January 11, 2010.
Activation of Warning Indicator Lights
(h) For airplanes identified in Boeing Alert Service Bulletin
737-31A1398, dated January 7, 2010: Within 36 months after the
effective date of this AD, activate the cabin altitude warning and
takeoff configuration warning lights, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
31A1398, dated January 7, 2010.
Airplane Flight Manual (AFM) Revisions
(i) Before further flight after doing the installation or
activation of the warning lights required by paragraph (g) or (h) of
this AD, do the actions specified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD.
(1) Revise the Limitations Section of the applicable Boeing 737
AFM by doing the actions specified in paragraphs (i)(1)(i) and
(i)(1)(ii) of this AD.
(i) Delete the ``CABIN ALTITUDE WARNING TAKEOFF BRIEFING'' added
by AD 2008-23-07.
(ii) Add the following statement. This may be done by inserting
a copy of this AD into the applicable AFM.
``For airplanes approved for maximum takeoff and landing
altitudes above 8,400 feet pressure altitude, change the limitation
for Maximum Takeoff and Landing pressure altitude as follows: With
the CABIN ALTITUDE and TAKEOFF CONFIG lights installed and operative
on those airplanes without the High Altitude Landing switch
installed, maximum takeoff and landing altitude is limited to 9,000
feet pressure altitude.''
[[Page 48623]]
(2) Revise the Emergency Procedures Section of the applicable
Boeing 737 AFM by doing the actions specified in paragraphs
(i)(2)(i), (i)(2)(ii), (i)(2)(iii), and (i)(2)(iv) of this AD.
(i) Delete the procedure ``WARNING HORN--CABIN ALTITUDE OR
CONFIGURATION'' added by AD 2006-13-13.
(ii) Delete the procedure entitled ``CABIN ALTITUDE WARNING OR
RAPID DEPRESSURIZATION'' added by AD 2006-13-13.
(iii) If the procedure entitled ``CABIN ALTITUDE (Airplanes with
the CABIN ALTITUDE lights installed)'' is currently contained in the
applicable Boeing 737 AFM, delete the procedure entitled ``CABIN
ALTITUDE (Airplanes with the CABIN ALTITUDE lights installed).''
(iv) Add the following statement. This may be done by inserting
a copy of this AD into the applicable AFM.
``CABIN ALTITUDE WARNING OR RAPID DEPRESSURIZATION (required by
this ad)
Condition: The CABIN ALTITUDE warning light illuminates or the
intermittent warning horn sounds in flight above 10,000 ft MSL.
RECALL:
Oxygen Masks and Regulators............ On, 100%
Crew Communications.................... Establish
REFERENCE:
Pressurization Mode Selector........... Manual
Outflow Valve Switch................... Close
Passenger Oxygen (If Required)......... On
Descent (If Required).................. Initiate
(3) Revise the Normal Procedures Section of the applicable
Boeing 737 AFM by doing the actions specified in paragraphs
(i)(3)(i) and (i)(3)(ii) of this AD.
(i) Delete the ``CABIN ALTITUDE WARNING TAKEOFF BRIEFING''
procedure added by AD 2008-23-07.
(ii) Add the following statement. This may be done by inserting
a copy of this AD into the applicable AFM.
``For normal operations, the pressurization mode selector should
be in AUTO prior to takeoff. (Required by this AD)''
Note 1: When statements identical to those specified in
paragraphs (i)(1)(ii), (i)(2)(iv), and (i)(3)(ii) of this AD have
been included in the general revisions of the AFM, the general
revisions may be inserted into the AFM, and the copies of this AD
may be removed from the AFM.
Terminating Action for Affected ADs
(j) Accomplishment of the requirements of this AD terminates the
specified requirements of the ADs identified in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD, for only the airplanes identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) AD 2008-23-07: All requirements of that AD.
(2) AD 2006-13-13: All requirements of that AD.
(3) AD 2003-03-15 R1: The requirements specified in paragraph
(a), Table 2, and Figures 2 and 3 of that AD.
Special Flight Permit
(k) Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Jeffrey W. Palmer, Aerospace Engineer, Systems and Equipment
Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6472; fax (425) 917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Issued in Renton, Washington, on July 28, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-19834 Filed 8-10-10; 8:45 am]
BILLING CODE 4910-13-P
